РАМНЫЙ ЭЛЕМЕНТ, СИСТЕМА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА ВОЗДУШНОГО СУДНА И СПОСОБ УСТАНОВКИ РАМНОГО ЭЛЕМЕНТА В ВОЗДУШНОМ СУДНЕ

Группа изобретений относится к области кондиционирования воздуха в воздушных судах. Рамный элемент для использования в системе кондиционирования воздуха выполнен с возможностью прикрепления к конструкции воздушного судна и включает в себя по меньшей мере одну продольную стойку, выполненную по меньшей мере на участках в виде полого цилиндра. Один из соединительных патрубков для подвода воздуха в стойке рамного элемента может быть присоединен к каналу для отвода воздуха установки кондиционирования воздуха воздушного судна, а другой соединительный патрубок для выпуска воздуха в стойке рамного элемента - к отверстию для выпуска воздуха, выходящему в область салона воздушного судна. Имеется по меньшей мере одна соединительная стойка, проходящая по меньшей мере на участках между двумя продольными стойками. Группа изобретений обеспечивает простую и быструю установку вентиляционных стояков в воздушном судне. 3 н. и 19 з.п. ф-лы, 10 ил.

УСТАНОВКА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА ДЛЯ ВОЗДУШНОГО СУДНА, ИМЕЮЩЕГО МНОЖЕСТВО КЛИМАТИЧЕСКИХ ЗОН С ИНДИВИДУАЛЬНЫМ РЕГУЛИРОВАНИЕМ ТЕМПЕРАТУРЫ

Изобретение относится к области авиационной техники. Установка (22) кондиционирования воздуха для воздушного судна (10), имеющего множество климатических зон (с 12 по 20) с индивидуальным регулированием температуры, содержит основную ответвляющуюся систему (26), содержащую систему (24) каналов подачи воздуха со смесительной камерой (28) и множеством разветвляющихся подсистем (30), средства (32) базового регулирования температуры, средства (36, 38, 40, 42) индивидуального регулирования температуры. Средства (36, 38, 40, 42) индивидуального регулирования температуры используются для индивидуального регулирования температуры подаваемого воздуха в каждой из разветвляющихся подсистем (30) в зависимости от желаемого значения температуры соответствующей климатической зоны и содержат один комбинированный теплоэнергетический двигатель (44), работающий в соответствии с термодинамическим циклическим процессом. Достигается экономичное кондиционирование воздуха многозонного пространства. 10 з.п. ф-лы ...

ВОЗДУХОРАСПРЕДЕЛИТЕЛЬНАЯ СИСТЕМА, СПОСОБЫ И УСТРОЙСТВА

Изобретение относится к устройствам для рассеивания воздуха внутри летательного аппарата. Воздухораспределитель содержит входную секцию с открытой внутренней частью, передним по потоку входным концом и задним по потоку входным концом, горловинную секцию с открытой внутренней частью, выходную секцию с открытой внутренней частью, внутреннюю пластину с отверстиями и внутренний дефлектор. Воздухораспределитель выполнен с возможностью создания уровня шумовых помех, затрудняющего речевое общение, меньше 50 дБ, когда воздух протекает через входную секцию к выходной секции с расходом больше 700 г/мин. Достигается обеспечение тишины и комфортных условий внутри салона летательного аппарата, а также протекание воздуха с расходом, который отвечает минимальным нормам для подачи свежего воздуха с комфортным расходом и обеспечением комфортного уровня шума. 2 н. и 13 з.п. ф-лы, 8 ил.

СИСТЕМА И СПОСОБ ОХЛАЖДЕНИЯ УСТРОЙСТВА НА БОРТУ ВОЗДУШНОГО СУДНА

Группа изобретений относится к технике распределения воды для снабжения пассажиров на борту воздушного судна охлажденной питьевой водой. Система распределения охлажденной питьевой воды включает в себя испаритель в виде бака для хранения питьевой воды, служащий для приема подлежащей испарению питьевой воды. Испаритель соединен с магистралью подачи питьевой воды для подачи питьевой воды в испаритель и кран для отбора охлажденной питьевой воды из испарителя. Кроме того, имеются: первый поглотитель, содержащий среду для поглощения питьевой воды, испаренной в испарителе, второй поглотитель, содержащий среду для поглощения питьевой воды, испаренной в испарителе, и система управления, выполненная с возможностью установления или прерывания соединения по потоку между испарителем и первым и/или вторым поглотителем (поглотителями). Группа изобретений позволяет распределять питьевую воду с надежным и непрерывным охлаждением. 2 н.з. и 10 з.п. ф-лы, 4 ил.

УСТРОЙСТВО ДЛЯ УВЛАЖНЕНИЯ ВОЗДУХА В КАБИНЕ ПАССАЖИРСКОГО ИЛИ ГРУЗОВОГО ВОЗДУШНОГО СУДНА

Изобретение относится к системам увлажнения воздуха в кабине пассажирского или грузового воздушного судна. Увлажняющее устройство позволяет производить индивидуальное увлажнение воздуха в кабине пассажирского или грузового воздушного судна путем нагнетания в кабину воздушного судна из выпускной форсунки кондиционирующей текучей среды. Кондиционирующая текучая среда в качестве составляющей содержит воду, которая распыляется в точке впрыска в непосредственной близости от выпускной форсунки. Кондиционирующая текучая среда содержит подводимую к выпускной форсунке воздушную струю, в которую осуществляется впрыск воды. Воздушная струя подается к точке впрыска при температуре, которая на заданную величину превышает требуемую эффективную температуру воздушной струи после ее выхода из выпускной форсунки. В другом варианте осуществления изобретения кондиционирующая текучая среда содержит воду в качестве единственного компонента, при этом распыление воды производится при температуре, превышающей температуру ...

СИСТЕМА ПОВЫШЕНИЯ ДАВЛЕНИЯ И КОНДИЦИОНИРОВАНИЯ ВОЗДУХА

Изобретение относится к области транспортного машиностроения, в частности к системам кондиционирования воздуха. Система повышения давления и кондиционирования воздуха содержит компрессор для повышения давления воздушного потока, который отбирается из канала набегающего потока наружного воздуха и через теплообменники подается в герметизированные зоны летательного аппарата. Для каждой зоны с различными температурами воздуха предусмотрен отдельный зонный теплообменник для подачи в нее дополнительного воздуха в соответствии с температурой, которая должна поддерживаться в зоне. Зонные теплообменники установлены в канале набегающего воздушного потока для охлаждения воздуха для отдельных зон до необходимой температуры. Достигается повышение эффективности охлаждения воздушного потока. 4 з.п. ф-лы, 3 ил.

СПОСОБ И УСТРОЙСТВО ДЛЯ КОНДИЦИОНИРОВАНИЯ ВОЗДУХА В КАБИНЕ ВОЗДУШНОГО СУДНА

Изобретение относится к области транспортного машиностроения, в частности к способам и устройствам кондиционирования воздуха в кабине воздушного судна. Способ кондиционирования воздуха в кабине воздушного судна заключается в том, что в кабину посредством одного нагнетателя направляют одну воздушную струю. Направление и импульс указанной воздушной струи изменяют при помощи средств для изменения направления и импульса воздушной струи в зависимости от температуры воздуха. Температуру воздуха измеряют при помощи средств для изменения направления и импульса воздушной струи. Устройство для кондиционирования воздуха в кабине воздушного судна содержит средства для формирования и направления одной воздушной струи и средства для изменения направления и импульса воздушной струи в зависимости от температуры воздуха. Средства для изменения направления и импульса воздушной струи выполнены с возможностью измерения температуры воздуха. Достигается повышение уровня теплового комфорта за счет средств для ...

ВЕНТИЛЯЦИОННАЯ СИСТЕМА С РАЗДЕЛЕНИЕМ ВОЗДУШНОЙ СТРУИ

Изобретение относится к вентиляционным системам летательных аппаратов. Вентиляционная система (100) включает в себя первый воздуховод (106, 107, 108), сообщающийся по текучей среде с первым источником (102, 104) воздуха в воздушном летательном аппарате, чтобы направлять поток текучей среды от первого источника воздуха. Вентиляционная система также включает в себя первое ответвление (110), сообщающееся по текучей среде с первым воздуховодом (106, 107, 108) и первым местом выпуска. Первое ответвление (110) снабжено устройством для активного перемещения воздуха. Вентиляционная система также включает в себя второе ответвление (112), выполненное отдельно от первого ответвления (110) и сообщающееся по текучей среде с первым воздуховодом (106, 107, 108) и вторым местом выпуска. Второе ответвление снабжено устройством для пассивного перемещения воздуха. Изобретение уменьшает габариты и вес, а также снижает потребление энергии. 3 н. и 17 з.п. ф-лы, 2 ил.

ЗВУКОПОГЛОЩАЮЩЕЕ УСТРОЙСТВО ДЛЯ ВОЗДУХОВОДА САМОЛЕТА

Устройство предназначено для снижения уровня шума в воздуховодах. Устройство содержит, по меньшей мере, один изогнутый отрезок трубы, внутренняя стенка которого плакирована звукопоглощающим материалом, при этом внутри изогнутого отрезка трубы расположено, по меньшей мере, одно средство направления воздуха для оптимизации течения, выполненное в виде акустического сепаратора, листовой металлический кожух которого охватывает центральный поглощающий сердечник и содержит микроперфорации в области внутренней боковой поверхности или внешней боковой поверхности, причем не перфорированная внутренняя боковая поверхность или внешняя боковая поверхность листового металлического кожуха содержит обычные перфорации, с относительной площадью поверхности перфораций, составляющей, по меньшей мере, 20%. Технический результат - повышение коэффициента звукопоглощения. 4 з.п. ф-лы, 2 ил.

СИСТЕМА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА ГЕРМЕТИЧЕСКОЙ ЗОНЫ ЛЕТАТЕЛЬНЫХ АППАРАТОВ

Изобретение относится к системам кондиционирования воздуха (СКВ) летательных аппаратов. Система кондиционирования воздуха содержит первичный и вторичный теплообменники, петлевые теплообменники и основной турбохолодильник. Система дополнительно содержит обводной трубопровод, подключенный через заслонку после первичного теплообменника, и содержащий дополнительный турбохолодильник, подключенный по входу в компрессор и по входу в турбину к трубопроводу отбора воздуха от двигателя, при этом выход компрессора включен в основной трубопровод перед вторичным теплообменником, а выход турбины подключен к зоне атмосферного давления. Достигается обеспечение достаточной степени сжатия воздуха в компрессоре турбохолодильника при пониженном давлении поступающего в систему воздуха. 1 ил.

СОПЛО, ОБЕСПЕЧИВАЮЩЕЕ ТРЕХМЕРНЫЙ СУЖАЮЩИЙСЯ ВОЗДУШНЫЙ ПОТОК, И СПОСОБ ИСПОЛЬЗОВАНИЯ ТАКОГО СОПЛА

Изобретение относится к распределению воздуха в летательном аппарате. Сопловое устройство (100) включает в себя корпус (105) сопла, имеющий пару противоположных боковых стенок (110), а также переднюю (115) и заднюю стенки, которые образуют воздушный проточный канал (125). Воздушный проточный канал (125) имеет осевую линию (130), проходящую между входным отверстием и выходным отверстием, и имеет множество поперечных сечений, перпендикулярных осевой линии, которые совместно образуют гладкий контур вдоль длины воздушного проточного канала. Каждое поперечное сечение имеет толщину между передней и задней стенками, которая больше на боковых кромках, чем на осевой линии (130). Толщина поперечных сечений уменьшается вдоль длины по меньшей мере первой части (145) корпуса (105) сопла. Ширина каждого из поперечных сечений между боковыми стенками увеличивается вдоль длины по меньшей мере первой части (145) корпуса (105) сопла. Достигается обеспечение необходимого объемного расхода кондиционированного ...

ПАТРУБОК ГИБКИЙ ИЗ ПОЛИМЕРНЫХ КОМПОЗИЦИОННЫХ МАТЕРИАЛОВ И СПОСОБ ЕГО ИЗГОТОВЛЕНИЯ НА ОСНОВЕ ВУЛКАНИЗИРОВАННОЙ ПРОРЕЗИНЕННОЙ СТЕКЛОТКАНИ И ПОЛИМЕРНОГО ПОКРЫТИЯ

Группа изобретений относится, в частности, к однослойным армированным композитным трубам, изготовленным на основе вулканизированной прорезиненной стеклоткани, предназначенным для транспортировки газообразных веществ в системах распределения воздуха аэрокосмической техники. Патрубок гибкий состоит из спиральной (гибкой) основной части, включающей внутреннюю оболочку из разных вариантов вулканизированной прорезиненной стеклоткани, спирали из кремнеземного наполненного шнура, окружающего ее базового композитного материала, защитной полимерной оболочкой двух манжет, изготовленных контактным формованием по месту, выполненных из стеклоткани конструкционной, пропитанной эластичным полимером, или из смеси резиновой, и предназначенных для соединения патрубка в рабочем положении на объекте. Техническим результатом изобретения является улучшение эксплуатационных характеристик особенно при эксплуатации патрубка при низких температурах, ремонтопригодность, простота монтажа и эксплуатации. Технический ...

Нагнетатель воздуха для системы кондиционирования воздуха летательного аппарата

Изобретение относится к атмосферной авиационной системе кондиционирования воздуха (СКВ) летательных аппаратов (ЛА) и касается нагнетателя наружного воздуха для СКВ ЛА. Нагнетатель воздуха выполнен на базе вентиляторной газодинамической двигательной установки, приводящийся в движение от приводного вала вентилятора, выполненного по схеме импеллера, с приемным устройством наружного воздуха в виде отверстия в обтекателе вентилятора. Причем внутри цилиндрической ступицы вентилятора сформированы внутренние поверхности, образующие продольные каналы для прохождения воздуха, поступающего от приемного устройства. При этом к наружной стороне ступицы прикреплены лопасти под углом к оси вентилятора, изготовленные с проходной продольной полостью, с образованием отверстий, обеспечивающих сообщение между полостью каждой лопасти и каналами в цилиндрической ступице вентилятора. Достигается упрощение конструкции системы обеспечения СКВ воздухом высокого давления при достижении сниженных потребляемой мощности ...

Система регулирования температуры воздуха в отсеке летательного аппарата

Система регулирования температуры воздуха в отсеке летательного аппарата, содержащая теплообменник, турбохолодильник и влагоотделитель, последовательно соединенные в магистрали подачи воздуха, исполнительный механизм регулятора температуры, установленный в обводном трубопроводе, подключенном к участку магистрали подачи перед влагоотделителем, и блок управления с датчиками температуры воздуха в отсеке и в магистрали подачи за влагоотделителем, отличающаяся тем, что, с целью повышения надежности работы путем предотвращения обмерзания выхода турбохолодильника и влагоотделителя, система снабжена датчиком промежуточной температуры охлаждаемого воздуха на входе турбохолодильника и обводного трубопровода и промежуточным сумматором, к входам которого подключены датчики промежуточной температуры охлаждаемого воздуха и воздуха в магистрали подачи за влагоотделителем, а к выходу - блок управления исполнительным механизмом регулятора температуры.

Влагоотделитель

Влагоотделитель, содержащий корпус с входным патрубком, размещенное в корпусе лопастное колесо, а на выходе из него - влагосборную камеру, и коагулятор, отличающийся тем, что, с целью повышения его эксплуатационной надежности при одновременном повышении эффективности влагоотделения, входной патрубок выполнен с окнами на боковой поверхности и снабжен сильфоном, входящим в эти окна, а коагулятор размещен в сильфоне со стороны корпуса.

Система кондиционирования воздуха на летательном аппарате

Система кондиционирования воздуха на летательном аппарате, содержащая теплообменник и влагоотделитель на трубопроводе высокого давления перед турбохолодильником и влагоотделитель на трубопроводе низкого давления за турбохолодильником, а также магистраль, сообщающую жидкостную полость влагоотделителя на трубопроводе высокого давления с устройством для впрыска отделенной влаги, отличающаяся тем, что, с целью повышения комфортности за счет отделения мелкодисперсной влаги путем интенсификации ее коагуляции, устройство для впрыска отделенной влаги установлено на трубопроводе низкого давления между турбохолодильником и влагоотделителем.

Способ кондиционирования воздуха на летательном аппарате и система для его осуществления

... 1. Способ кондиционирования воздуха на летательном аппарате, включающий изменение весового расхода воздуха в соответствии с изменением давления и температуры кондиционированного воздуха в процессе ее регулирования, отличающийся тем, что, с целью повышения экономичности путем увеличения степени оптимизации расхода кондиционированного воздуха, дополнительно измеряют температуру наружного воздуха и при ее изменении весовой расход подаваемого воздуха изменяют обратно пропорционально изменению величины корня квадратного из алгебраической суммы температур кондиционированного и наружного воздуха. 2. Система кондиционирования воздуха на летательном аппарате, содержащая воздухоохладитель, регулятор температуры и регулятор расхода, включающий датчик температуры кондиционированного воздуха и измерительное устройство с датчиками абсолютной величины и перепада давлений воздуха, а также исполнительную заслонку и вычислитель расхода, связанный с датчиками, отличающаяся тем, что, с целью повышения экономичности ...

Влагоотделитель

Влагоотделитель, содержащий корпус с фланцами, входным и выходным патрубками, размещенные в корпусе завихритель, коагулятор в виде соосно установленных сетчатых цилиндра и усеченного конуса и перепускной плунжерный клапан, отличающийся тем, что, с целью повышения эксплуатационной надежности, усеченный конус коагулятора и корпус перепускного клапана снабжены кольцевыми выступами, корпус клапана снабжен прикрепленными к кольцевому выступу спицами и соединенным с ними периферийным ободом с цилиндрическим поясом с пазами, расположенным соосно ступице клапана, при этом кольцевой выступ усеченного конуса коагулятора и периферийный обод клапана размещены между фланцами корпуса, цилиндрический пояс прижат к внутренней поверхности корпуса, один из торцов корпуса клапана расположен внутри сетчатого цилиндра коагулятора, между поверхностями которых размещено уплотнительное кольцо, а завихритель соединен с цилиндрическим поясом посредством шлицевого соединения с контровкой разрезным кольцом.

Перекрывное устройство

Перекрывное устройство, содержащее корпус с гильзой, внутри которой установлен запорный орган, связанный с приводным валом, отличающееся тем, что, с целью упрощения конструкции и повышения надежности работы, наружная поверхность гильзы выполнена ступенчатой, одна из ступеней которой, контактирующая с корпусом, эксцентрична внутренней цилиндрической поверхности гильзы, установленной в корпусе с возможностью поворота и фиксирования в требуемом положении, а приводной вал запорного органа смонтирован в корпусе с возможностью свободного осевого перемещения.

Коагулятор для влагоотделителей

Коагулятор для влагоотделителей, содержащий перфорированный каркас с укрепленной на нем сеткой, например лавсановой, отличающийся тем, что, с целью регулирования натяжения сетки, в месте сгиба каркаса установлен обтекатель с регулирующим устройством, например винтовым, при этом в каркасе выполнены профилированные пазы с размещенными в них кольцами, обтянутыми сеткой.

Теплообменник

... 1. Теплообменник, содержащий пакет плоских труб с размещенными между ними гофрированными пластинами и отводящим коллектором в виде конфузора с центральным отверстием, отличающийся тем, что, с целью интенсификации теплообмена, пластины на участке, противолежащем отверстию, выдвинуты за пределы труб внутри коллектора на расстояние, уменьшающееся от оси конфузора к периферии пакета, а трубы установлены с шагом, возрастающим в том же направлении. 2. Теплообменник по п.1, отличающийся тем, что гофрированная пластина, лежащая по оси конфузора, выдвинута за пределы труб на расстояние, равное 3,28 где α - угол сужения конфузора.

Система кондиционирования воздуха в гермокабине самолета

Система кондиционирования воздуха в гермокабине самолета, содержащая воздухо-воздушный теплообменник с охлаждающей полостью, топливо-воздушный теплообменник с топливным каналом и межтрубным пространством, которые соединены трубопроводами с трубохолодильником и вихревой трубой, имеющей горячий и холодный концы и полость охлаждения, отличающаяся тем, что, с целью уменьшения веса и габаритов системы, в ней выход топливо-воздушного теплообменника соединен трубопроводом через холодный конец вихревой трубы с межтрубным пространством этого теплообменника и с атмосферой, в горячем конце вихревой трубы установлен эжектор, всасывающая полость которого соединена трубопроводом через полость охлаждения вихревой трубы с охлаждающей полостью воздухо-воздушного теплообменника, а топливный канал топливо-воздушного теплообменника соединен трубопроводом через полость охлаждения вихревой трубы с топливной магистралью.

Установка для кондиционирования воздуха

... 1. Установка для кондиционирования воздуха, например, в летательных аппаратах, имеющая во входном воздуховоде конденсаторно-компрессорный блок с вентилятором, распределительный воздуховод с вентиляционноиспарительным блоком, отличающаяся тем, что, с целью снижения энергозатрат на обработку воздуха и повышения эффективности поддержания его температуры, установка выполнена с дополнительным, также имеющим вентиляционноиспарительный блок распределительным воздуховодом, соединенным с основным, в каждом из которых размещен присоединенный к датчику температуры воздуха клапан, причем конденсаторно-компрессорный блок с вентилятором дополнительного воздуховода также установлен во входном воздуховоде, в котором укреплена образующая параллельные отсеки перегородка. 2. Установка по п.1, отличающаяся тем, что вентиляторы конденсаторно-компрессорных блоков присоединены к датчику давления, установленному во входном воздуховоде.

Испытательный комплекс для высотных систем регулирования температуры воздуха

Испытательный комплекс для высотных систем регулирования температуры воздуха, содержащий источники наддува и разрежения, трубопроводы подачи воздуха с включенными в них агрегатами воздухоподготовки по температуре и давлению и измерительную аппаратуру, отличающийся тем, что, с целью повышения экономичности и обеспечения возможности испытаний систем, использующих токсичный хладагент, в нем источник наддува выполнен в виде газотурбинного двигателя, компрессор которого при помощи трубопроводов через агрегаты воздухоподготовки подключен к агрегатам испытуемой системы, а через исполнительный орган с программным управлением - к источнику разрежения, выполненному в виде эжектора, выход которого соединен с атмосферой, а к камере смешения подключена заполненная нейтрализующей жидкостью емкость, соединенная с испарительной полостью теплообменника испытуемой системы.

ДРЕНАЖНОЕ УСТРОЙСТВО

СПОСОБ ОБОГАЩЕНИЯ ДЫХАТЕЛЬНОЙ СМЕСИ ДЛЯ ЧЛЕНА ЭКИПАЖА ЛЕТАТЕЛЬНОГО АППАРАТА

Изобретение относится к средствам обогащения дыхательной смеси для членов экипажа летательного аппарата. Цель изобретения - улучшение условий жизнедеятельности члена экипажа путем изменения степени обогащения соответственно изменению высоты полета. В каждом цикле при сорбции азота из воздуха в одном и адсорберов 1 или 2 в другом адсорбере осуществляют регенерацию адсорбента. Блоки управления 16 и 17 связаны с датчиками 14 и 15 абсолютного давления обогащаемой смеси в адсорберах и с приводами клапанов. Блоки управления 20 и 21 связаны с датчиками 18 и 19 избыточного относительно атмосферного давления газа, сбрасываемого в атмосферу при регенерации адсорбента, и с приводами клапанов. Перед окончанием сорбции азота в каждом цикле регенерируемый адсорбент продувают частью обогащенной смеси. При высотном маневре летательного аппарата предельные величины наибольшего абсолютного давления обогащаемой смеси и наименьшего избыточного давления сбрасываемого газа поддерживают постоянными. Вследствие ...

УСТАНОВКА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА ДЛЯ ВОЗДУШНОГО СУДНА, ИМЕЮЩЕГО МНОЖЕСТВО КЛИМАТИЧЕСКИХ ЗОН С ИНДИВИДУАЛЬНЫМ РЕГУЛИРОВАНИЕМ ТЕМПЕРАТУРЫ

... 1. Установка кондиционирования воздуха (22) для воздушного судна (10) или других помещений, имеющих множество климатических зон (12-20) с индивидуальным регулированием температуры, содержащая: ! систему (24) каналов подачи воздуха со смесительной камерой (28) и множеством разветвляющихся подсистем (30), отходящих от смесительной камеры и в каждом случае ведущих к одной из климатических зон, ! средства (32) базового регулирования температуры для регулирования температуры подаваемого воздуха в смесительной камере (28) в зависимости, по меньшей мере, от одного желаемого значения температуры, ! средства (36, 38, 40, 42) индивидуального регулирования температуры для индивидуального регулирования температуры подаваемого воздуха в каждой из разветвляющихся подсистем (30) в зависимости от желаемого значения температуры соответствующей климатической зоны, отличающаяся тем, что средства индивидуального регулирования температуры, предназначенные, по меньшей мере, для одной из климатических зон (20 ...

Система кондиционирования воздуха

Система кондиционирования воздуха, содержащая воздухо-воздушный и топливо-воздушный теплообменники, влагоотделитель и турбохолодильник, последовательно соединенные между собой по линии подачи воздуха, и парокомпрессионную установку с компрессором, конденсатором, выполненным в виде топливного теплообменника, и испарителем, вход которого по воздуху подключен к выходу топливо-воздушного теплообменника, а выход - к входу влагоотделителя, отличающаяся тем, что вход конденсатора по топливу соединен с выходом топливо-воздушного теплообменника.

СИСТЕМА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА ДЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА С ИОНИЗАТОРОМ

Система кондиционирования воздуха для летательного аппарата с ионизатором, содержащая магистраль горячего воздуха с установленным в ней дроссельным устройством, магистраль холодного воздуха с последовательно установленным в ней дроссельным устройством, датчиком температуры, влагоотделителем, а также датчик температуры, установленный в гермокабине и связанный со входом третьего регулятора температуры, управляющего третьим дроссельным устройством, установленным в магистрали после соединения горячей и холодной линий, перед которым располагается датчик температуры, отличающаяся тем, что в магистрали, перед гермокабиной, после дроссельного устройства, установлен ионизатор отрицательных ионов, выполненный в виде иголок ромбовидной или круглой формы в поперечном сечении, расположенных радиально и закрепленных одним концом, с большим сечением, к металлическому кольцу, изолированному электрически от других элементов, и которое соединено с отрицательной клеммой постоянного источника тока напряжением ...

СИСТЕМА УЛУЧШЕНИЯ КАЧЕСТВА ВОЗДУХА В ГЕРМЕТИЧЕСКОЙ КАБИНЕ ВОЗДУШНОГО СУДНА

... 1. Система улучшения качества воздуха в герметической кабине воздушного судна, в которой часть воздуха кабины, так называемый воздух рециркуляции, извлекают из герметической кабины в контур рециркуляции воздуха, подвергают кондиционированию и затем возвращают в герметическую кабину, при этом ! определенное количество воздуха рециркуляции пропускают, целиком или частично, через генератор (52) азота, который из подаваемого воздуха рециркуляции производит азотосодержащий и кислородосодержащий отработавшие газы, ! кислородосодержащий отработавший газ, произведенный генератором (52) азота, вместе с остальным количеством воздуха рециркуляции, не прошедшим обработку генератором (52) азота, возвращают в герметическую кабину, причем ! в генератор (52) азотаподают только воздух рециркуляции, ! отличающаяся тем, что ! генератор (52) азота использует для выработки азота исключительно градиент давления, существующий в полете на высотах, отличных от малых высот полета или от уровня земли, между герметической ...

РЕГУЛЯТОР РАСХОДА ВОЗДУХА

СИСТЕМА КОНДИЦИОНИРОВАНИЯ ВОЗДУХА НА ЛЕТАТЕЛЬНОМ АППАРАТЕ

... 1. Система кондиционирования воздуха на летательном аппарате, содержащая параллельные линии отбора воздуха от компрессоров двигателей, линию кольцевания и параллельные линии подачи воздуха в кабину, при этом каждая линия отбора и подачи воздуха включает мерное устройство, вычислитель, командный прибор, выход которого соединен с исполнительным механизмом, а в линиях подачи воздуха в кабину выполнены холодный и теплый каналы, отличающаяся тем, что, с целью повышения надежности работы, упрощения монтажа и эксплуатации системы, каждая линия отбора воздуха соединена с одной линией подачи воздуха в кабину, а линия кольцевания снабжена штуцером запуска и нормально закрытыми заслонками, установленными между линиями отбора, и соединена с воздушным стартером каждого двигателя и через обратный клапан и регулирующую заслонку с бортовым вспомогательным компрессором, а теплые каналы соединены между собой через обратные клапаны, с атмосферой через предохранительный и обратный клапаны и с дополнительно ...

Влагоотделитель

Изобретение относится к влагоотделителям для системы кондиционирования воздуха. Целью изобретения является улучшение эксплуатационных характеристик путем интенсификации отделения влаги при уменьшении габаритоа Промежуточный сепаратор 4 установлен между входным патрубком 2 и цилиндрическим воздуховодом 1 с каналом для отвода влаги. Промежуточный сепаратор 4 выполнен в виде конусообразной поверхности. Эта поверхность сформирована перемещением прямолинейной образующей переменной длины из вершины 5 через винтовую кромку цилиндрического воздуховода . 1 ал. ф-лы, 4 ил.

ТУРБОХОЛОДИЛЬНОЕ ВЛАГООТДЕЛЯЮЩЕЕ УСТРОЙСТВО

Турбохолодильное влагоотделяющее устройство, преимущественно для систем кондиционирования воздуха летательных аппаратов, содержащее установленные последовательно на одном валу расширительную турбину, снабженную выходным диффузором, и конический коагулятор, размещенные в корпусе, имеющем влагосборник и соосный с коагулятором патрубок для отвода осушенного воздуха, отличающееся тем, что, с целью повышения эффективности отделения мелкодисперсной влаги, конический коагулятор расположен вершиной к выходному диффузору турбины, а основанием - к лабиринтному уплотнению, выполненному на внутреннем торце патрубка для отвода осушенного воздуха.

УСТРОЙСТВО ДЛЯ РЕГУЛИРОВАНИЯ ДАВЛЕНИЯ В ГЕРМОКАБИНЕ ЛЕТАТЕЛЬНОГО АППАРАТА

Устройство для регулирования давления в гермокабине летательного аппарата, содержащее группу выпускных клапанов, управляющие элементы, переключатели с нормально открытыми и нормально закрытыми каналами и реле давления, отличающееся тем, что, с целью повышения надежности работы устройства, в нем к нормально закрытому каналу переключателя каждого выпускного клапана подключены динамическая полость реле давления этого же клапана и управляющий элемент последующего выпускного клапана, причем нормально закрытый канал переключателя последнего выпускного клапана соединен с управляющим элементом первого клапана, а статическая полость реле давления каждого клапана подсоединена к управляющему элементу этого же клапана.

РЕЗЕРВНАЯ СИСТЕМА ОХЛАЖДЕНИЯ ВОЗДУШНОГО СУДНА ДЛЯ ОХЛАЖДЕНИЯ РЕЗЕРВНЫХ КОМПОНЕНТОВ ВОЗДУШНОГО СУДНА

... 1. Система (1) охлаждения воздушного судна, содержащая первый поток (4а) теплоносителя для охлаждения, по меньшей мере, одной первой тепловой нагрузки (2а), и второй поток (4b) теплоносителя для охлаждения, по меньшей мере, одной второй тепловой нагрузки (2b), причем первая тепловая нагрузка (2а) и вторая тепловая нагрузка (2b) образованы двумя взаимно резервирующими компонентами воздушного судна, отличающаяся тем, что первая тепловая нагрузка (2а) и вторая тепловая нагрузка (2b) двунаправленно термически соединены друг с другом. ! 2. Система по п.1, отличающаяся тем, что выполнена с возможностью охлаждения первой тепловой нагрузки (2а) и второй тепловой нагрузки (2b) первым потоком (4а) теплоносителя и вторым потоком (4b) теплоносителя по очереди. ! 3. Система по п.1 или 2, отличающаяся тем, что предусмотрен третий поток (12) теплоносителя, причем первая тепловая нагрузка (2а) и вторая тепловая нагрузка (2b) термически соединены посредством указанного третьего потока. ! 4. Система по п ...

Исполнительный клапан системы регулирования давления воздуха в термокабине летательного аппарата

Регулятор избыточного давления газа

Распределительный кран

Устройство для увлажнения воздуха при подаче его в гермокабину летательного аппарата

Система увлажнения воздуха

Регулятор давления

Турбоагрегат для систем кондиционирования воздуха летательных аппаратов

Аппарат для термовлажностной обработки воздуха

Изобретение относится к аппаратам для термовлажностной обработки воздуха. Целью изобретения является повышение эффективности использования воздуха высокого давления. Перед тангенциальным соплом 2 вихревой трубы установлен воздухо- жидкостной смеситель 8. Смеситель 8 через дозатор 9 соединен с баком 10 для воды. Вход смесителя 8 и надводяное пространство бака 10 соединено с воздухопроводом 3 высокого давления. Канал 1 энергетического разделения в вихревой трубе заключен между каналом 4 для выпуска горячего воздуха и диафрагмой 5 перед патрубком 6 для выпуска холодного воздуха. В канале 4 установлен регулирующий клапан 13. Патрубок 6 сообщен со смесителем 7 эжекторного типа . Выход смесителя 7 обращен наружу из канала 1. Коаксиально каналу 1 расположен канал 11 возврата увлажненного горячего воздуха. Канал 4 соединен со смесителем 7 через канал 11.1 з.п. ф-лы, 1 ил.

Турбохолодильник для систем кондиционирования

Влагоотделитель

Газоструйный щелевой инжектор для систем кондиционирования воздуха

INTEGRIERTE STROMVERSORGUNG UND KLIMAREGELUNGSSYSTEM

KALTLUFTVERFAHREN.

Vorrichtung und Verfahren zur Abluftkühlung von Flugzeugklimaanlagen

Vorrichtung zur Abluftkühlung von Flugzeugklimaanlagen mit einem Bypasskanal (20), welcher einen einem Stauluftkanal (30) mit einem Staulufteinlass-Kanalabschnitt (32) nachgeschaltet angeordneten Wärmetauscher einer Flugzeugklimaanlage (10) umgeht, und welcher in einen Auslasskanal (40) zum Auslassen von im Wärmetauscher (10) erwärmter Stauluft, der dem Wärmetauscher nachgeschaltet angeordnet ist, vor einer Austrittsöffnung (42) für Abluft einmündet, um kalte Stauluft in den Abluftstrom zu befördern, wobei für den Stauluftkanal (30) und den Bypasskanal (20) ein gemeinsamer Einlass (25) vorgesehen ist.

Fluid orifice for controlling flow of fluid, has plurality of friction elements whereby fluid flowing against fluid orifice in its flow rate is continuously restricted by extension of fluid orifice towards flow direction

The fluid orifice (2) has plurality of friction elements (3) extending in a direction of flow of pipes (4). The individual friction elements from plurality of friction elements are arranged in such a manner that a fluid flowing against the fluid orifice in its flow rate (Q) is continuously restricted by the extension of the fluid orifice towards the flow direction due to the friction at the individual frictional parts. Independent claims are included for the following: (1) Application of fluid orifice; and (2) Air-conditioner in an airplane.

Luftfahrzeug-Klimatisierungssystem zum individuellen Klimatisieren von Bereichen einer Luftfahrzeugkabine mit einem flüssigen Kühlmittel

Luftfahrzeug-Klimatisierungssystem, mit einer Sitzzuführleitung (8), in der zumindest ein Wärmetauscher (14) und zumindest eine Heizeinrichtung (22) zur Klimatisierung eines zumindest einer Person zugeordneten Bereichs (2) einer Luftfahrzeugkabine angeordnet sind, wobei dem Wärmetauscher (14) ein in einem Kühlkreislauf eines Kühlsystems zirkulierendes Kühlmittel und Luft von einem zentralen Klimatisierungssystem des Luftfahrzeuges zugeführt werden, wobei das Kühlmittel im Wärmetauscher (14) die zugeführte Luft kühlt und die Heizeinrichtung (22) die in den Bereich (2) einströmende Luft erwärmt, wobei die aus der Sitzzuführleitung (8) austretende Luft in den Bereich (2) der Luftfahrzeugkabine eintritt und wobei sich das Kühlmittel des Kühlsystems in dem Kühlkreislauf ständig im flüssigen Zustand befindet.

Kühlsystem und Frachtcontainer

Ein System (10) zur Kühlung von Frachtgütern an Bord eines Flugzeugs umfasst eine Kälteerzeugungseinrichtung und eine Kühlstation (14), der mittels eines Kälteträgermediums von der Kälteerzeugungseinrichtung erzeugte Kühlenergie zugeführt wird und die mit einer Luftzufuhrleitung (29) einer Flugzeugklimaanlage verbunden ist, wobei eine Luftauslassöffnung (16) der Kühlstation (14) mit einem Frachtraum (24) des Flugzeugs verbindbar ist, um auf eine gewünschte Temperatur abgekühlte Luft in den Frachtraum (24) abzuleiten.

Klimatisierungssystem und Verfahren zur Aufbereitung von Luft zur Klimatisierung eines Raumes

Die vorliegende Erfindung betrifft ein Klimatisierungssystem, insbesondere ein Klimatisierungssystem zur Klimatisierung einer Passagierkabine eines Flugzeuges, mit wenigstens einem in einem Stauluftkanal angeordneten Wärmetauscher zur Kühlung von Druckluft sowie mit wenigstens einer ersten und einer zweiten Welleneinrichtung, wobei der Wärmetauscher wenigstens eine erste und eine davon druckluftseitig getrennte zweite Wärmetauschereinheit umfasst, die in dem gemeinsamen Stauluftkanal angeordnet sind und von denen jeweils eine druckluftseitig mit jeweils einer der Welleneinrichtungen in Verbindung steht, wobei die Welleneinrichtungen Verdichter aufweisen, die auslassseitig jeweils mit dem druckluftseitigen Einlass der Wärmetauschereinheiten in Verbindung stehen. Die Verdichter werden einlassseitig mit Stau- oder Umgebungsluft beaufschlagt und mittels eines oder mehrerer Motoren angetrieben. Die Erfindung betrifft ferner ein Verfahren zur Aufbereitung von Luft zur Klimatisierung eines Raumes ...

Bewegliches Objekt mit einem zu klimatisierenden Innenraum

Die Erfindung betrifft ein bewegliches Objekt mit mindestens einem Innenraum, der durch Bauelemente in Form eines Bodens, einer Decke und/oder Wänden zur Abgrenzung umgeben ist, wobei wenigstens eines der Bauelemente aus einem Faserverbundwerkstoff aufweisend wenigstens ein Fasermaterial und ein Matrixmaterial hergestellt sind und wobei das bewegliche Objekt eine Klimatisierungseinrichtung zur Klimatisierung des Innenraumes durch Zuführung von Zuluft in den Innenraum aufweist, wobei das aus dem Faserverbundwerkstoff gebildete Faserverbund-Bauelement eine Vielzahl von Öffnungen aufweist, die mit der Klimatisierungseinrichtung in Verbindung stehen, wobei die Klimatisierungseinrichtung zur Zuführung von Zuluft in den Innenraum des beweglichen Objektes über die in dem Faserverbund-Bauelement befindlichen Öffnungen ausgebildet ist.

Klimaregelungssystem

Luftführungselement für ein Luftverteilungssystem in einem Flugzeug, Steigrohr und Flugzeug damit

Die Erfindung betrifft ein Luftführungselement 10 für ein Luftverteilungssystem in einem Flugzeug. Das Luftführungselement 10 weist einen von Luft durchströmbaren Luftführungskörper 12 mit einem geschlossenen Strömungsquerschnitt auf. An einem ersten Ende des Luftführungskörpers 12 ist ein Lufteinlass 14 und einen an einem zweiten stromabwärts gelegenen Ende ist ein Luftauslass 16 ausgebildet. Erfindungsgemäß ist der Luftführungskörper 12 zumindest abschnittsweise aus einem flexiblen und fluiddichten Leitungsmaterial gebildet und in einem stromaufwärts des Luftauslasses 16 angeordneten Bereich sind gegenüberliegende Strömungswandabschnitte des Luftführungskörpers 12 mit einem oder mehreren den Strömungsquerschnitt durchquerenden Fäden verbunden.

Luftkreislauf- Klimaregelungssystem

System zum Abgeben von Luft aus einer Luftquelle in einer Passagierkabine eines Fahrzeugs

Es wird ein System zum Abgeben von Luft aus einer Luftquelle in einer Passagierkabine eines Fahrzeugs vorgeschlagen, aufweisend mindestens ein Ventil und mindestens eine mit dem Ventil verbindbare Spannungsquelle, wobei das Ventil in einem mit der Luftquelle in Fluidverbindung bringbaren Ventilsitz angeordnet ist, wobei das Ventil einen Ventilkörper besitzt, der ein durch Anlegen einer elektrischen Spannung verformbares, elektroaktives Polymer aufweist, wobei der Ventilkörper eine Grundform aufweist, die in einem spannungslosen Zustand den Ventilsitz zum Schließen vollständig überdeckt, und wobei der Ventilkörper dazu ausgebildet ist, bei Anlegen einer Spannung der Spannungsquelle durch Verformung des elektroaktiven Polymers zumindest teilweise den Ventilsitz zu öffnen, so dass Luft aus der Luftquelle durch das Ventil strömen kann.

KLIMAANLAGE MIT LUFTUMWAELZUNG

SYSTEM UND VERFAHREH ZUM KÜHLEN VON LUFT IN EINEM FLUGZEUG

Luftverteilungssystem

Ein Luftverteilungssystem weist eine Hauptversorgungsleitung (6), eine Mehrzahl von Luftauslässen (3), die über jeweilige Luftausblasstrecken an die Hauptversorgungsleitung (6) angeschlossen sind, und mindestens ein Heizelement (8), welches mindestens einem der Luftauslässe (3) zugeordnet ist und die Luft in der Ausblasstrecke dieses Luftauslasses (3) temperieren kann, auf.

Turbokompressor mit Luftlagerung und selbstschliessendem Luftversorgungsventil

Zonentemperaturregelung an Bord eines Flugzeuges mittels Brennstoffzellenabwärme

Die Erfindung betrifft ein Klimatisierungssystem für ein Verkehrsmittel mit mehreren zu klimatisierenden Zonen (20), die durch aufbereitete Zuluft in Verbindung mit individuellen Trimmluftleitungen (24) unterschiedlich klimatisiert werden können, wobei das Klimatisierungssystem ferner mindestens einen Wärmetauscher (32) aufweist, der Zuluft mittels der Wärme des Abgases einer Brennstoffzelle (36) erwärmt und in einen die Trimmluftleitungen (24) versorgenden Trimmluftverteiler (28) abgibt.

Flugzeug mit Flugzeugklimaanlage und Vorrichtung zur Luftversorgung der Flugzeugklimaanlage

Flugzeug mit mindestens einer Flugzeugklimaanlage (100) und mindestens einer Vorrichtung zur Luftversorgung der wenigstens einen Flugzeugklimaanlage (100), wobei die Vorrichtung einen ersten Lufteinlasskanal (10) und einen zweiten Lufteinlasskanal (20) aufweist, die eine Einlassöffnung (12, 22) aufweisen, durch die die Lufteinlasskanäle (10, 20) mit Umgebungsluft beaufschlagt werden und die auslassseitig unmittelbar oder mittelbar mit der Flugzeugklimaanlage (100) in Verbindung stehen, wobei die Einlassöffnung (22) des zweiten Lufteinlasskanals (20) durch eine Öffnung in der Außenhaut (50) des Flugzeuges gebildet wird, wobei die Vorrichtung eine verstellbare Klappe (30) aufweist, dadurch gekennzeichnet, dass die verstellbare Klappe (30) vor der als Lufeinlasshutze (14) gebildeten Einlassöffnung (12) des ersten Lufteinlasskanals (10) so angeordnet ist, dass sie relativ zu der Außenhaut (50) des Flugzeugs sowohl nach außen als auch nach innen auf- bzw. eingeklappt werden kann, so dass diese ...

A cab pressure warning system and method

A method for providing a cab 22 pressure warning signal to a vehicle operator, comprising monitoring the cab pressure level, providing a cab pressure warning signal to a operator if the monitored cab pressure level is below a threshold level, wherein the method further comprises monitoring a cab door status, to determine if the vehicle cab door 24 is opened or closed, wherein said cab pressure level warning signal is not provided to the operator if the cab door is open. The method may comprise monitoring a cab door activated switch 30 to determine if cab door is opened or closed. A cab door closure status may comprise monitoring a switch for a cab interior courtesy light. The method may comprise providing a positive cab pressure signal if the monitored cab pressure level is above a threshold level.

Air temperature conditioning system

... 609,823. Refrigerating. GARRETT CORPORATION. Sept. 18, 1945, No. 24032. Convention date, Oct. 11, 1944. [Class 29] [Also in Group X] In air cooling systems for air supplied under pressure to an enclosure such as an aircraft cabin, a cooling medium is circulated through a path independent of and in heat exchange relation with the air flow path by an air motor driven by air diverted from it. Air is delivered to a pressurized aircraft cabin 1 through a duct 3 and discharged through a pressure regulating valve 9 of an outlet 7. Air from an inlet 15 is driven by a fan 18 through the jacket 17 of an auxiliary engine 13 driving a supercharger 11 through which air from the jacket passes to the air passages 23 of an evaporator 25 of a refrigeration circuit, where the air passes to the supply duct. In a bye-pass 47, 49 an air turbine 45 drives the refrigerant compressor 29, the flow of air through the bye-pass being regulated by a valve 51 responsive to cabin temperature changes. The refrigerant ...

Enclosure air supply system

... 737,393. Ventilation. GARRETT CORPORATION. Sept. 23, 1952 [Oct. 18, 1951], No. 23802/52. Class 137. In an air supply system, particularly for an aircraft compartment, a compressor 9 for ambient air discharges to atmosphere through a cabin supply duct 14 and a cabin exhaust duct 18, 20, 28, 29, the exhaust duct including combustion-power means 26, 27 which drive the compressor, and a valve-controlled duct 12 connects the compressor to the combustion-power means, the air inlet 14 to the cabin also being valve controlled. The compressor 9 receives ambient air at 10 and passes it to a duct 11 which branches at 12 through the check valve 23 to the combustion chamber 26 supplying the gas turbine 27 which drives the compressor 9. The duct 11 further branches at 13, 14, the branch 13 being for supplying pneumatic devices such as the starting equipment for the main engines. The branch 14 leads to the cabin 16 in which the pressure is maintained and regulated by a conventional outflow valve 17. Exhaust ...

Air conditioning apparatus for aircraft

... 1,083,573. Fluid-pressure servomotor systems. BRISTOL SIDDELEY ENGINES Ltd. March 11, 1964 [March 12, 1963; June 20, 1963], Nos. 9793/63 and 24625/63. Heading G3P. [Also in Divisions B1 and F4] An air flow shut off and control valve assembly in the air conditioning system of an aircraft (see Division F4) comprises a shut off valve and a control valve in series in a casing 24 through which pressurized fresh air passes from the left as seen in Fig. 4. A shut off valve member 65 is connected to a piston 66 biased towards the open position by a spring 67 and towards the closed position by the connection of a chamber 68 through openings 69 and 70 with the pressurized air stream. The chamber 71 on the other side of the piston communicates through an opening 72 with the chamber 68. The valve is then open unless a relief passage 73 leading from the chamber 71 is opened by either of valves 73A or 73B (Fig. 5). The valve 73A is opened by energization of a solenoid 73C. The valve 73B is connected ...

Preventing the formation of ice on the interior surface of an aircraft fuselage shell

An aircraft fuselage shell structure comprises an interior space, and a heater 15, 22 disposed within the enclosed space adjacent the shell structure, the heater being adapted to drive moisture from air in a region immediately adjacent the structure to air in a region disposed from the structure within the enclosed space, thereby preventing condensation and the formation of ice on the shell interior surface. Moisture is ideally driven 20, 26 from between the shell skin inner wall and the cabin partition into the cabin. The heater may be in the form of a heater mat (figure 2) wherein heat pipes or electrical wiring 16 are supported by an layer 15 which is permeable to water vapour, but not to water, so that moisture gets wicked through the layer. Alternatively, the heater could be a hot air blower (figure 3) driving the moisture into the cabin compartment.

Aircraft air conditioning system

An air cycle air conditioning system has an air expansion turbine 12 arranged for supplying a flow of turbine expanded air for conditioning a heat load 19. Water extracted at 16 from high pressure supply air upstream of the air expansion turbine 12 is injected into the coolant flow entry 17 of a heat exchanger 15 arranged for receiving the flow of turbine expanded air after this air has extracted heat from the heat load 19 e.g. a cabin. This enhances the cooling efficiency of the system by making use of the latent heat of evaporation of the extracted water when this water is returned to the system in a region where it provides a coolant function. The heat exchanger 15 cools high pressure supply air between the compressor 13 and turbine 12 but, in an alternative embodiment, the heat exchanger receiving injected water into the coolant flow entry is in heat exchange relationship with a fluid circulating in a separate loop to cool a further heat load. ...

Aircraft air disinfection system

AIR CONDITIONING SYSTEMS

Aircraft propulsor

An aircraft propulsor 200 includes a nacelle 208, a fan (116, fig 1) and a core plug 218. The nacelle includes a leading edge 210 and a trailing edge 212 downstream of the leading edge defining a duct 214 therein. The fan is received within the duct and is configured to rotate about a rotational axis Y-Y’ and generate a primary fluid flow. The core plug is at least partially received within the nacelle and includes a boundary wall 220 radially inward of the nacelle so that the primary fluid flow from the fan passes between the nacelle and the boundary wall 220. The core plug extends axially beyond the trailing edge of the nacelle relative to the rotational axis (Y-Y’) of the fan. The boundary wall of the core plug includes a flow control feature 226 located downstream of the trailing edge of the nacelle for reducing boundary layer separation of the primary fluid flow. The flow control feature may be slots (228, figure 3), vortex generators (240, figure 5) or jet vortex generators (244, ...

Improvements in or relating to air conditioning systems for aircraft

... 1,011,045. Air conditioning aircraft; refrigerating. NORMALAIR Ltd. Jan. 7, 1964 [Jan. 24, 1963], No. 3021/63. Headings F4H and F4V. In an air conditioning system for an enclosure of an aircraft, fresh air is passed to the enclosure through a cooler and air is recirculated from the enclosure through the cooler, a portion of the recirculated air suffering removal of odours and carbon dioxide. As illustrated, fresh air bled from one or more compressors of the aircraft engines is passed through an air or fuel cooled heat exchanger 2 and split into three streams, one of which 4 passes to the enclosure through a heat exchanger 15 cooled by a refrigeration circuit, and the other two of which 5 and 6 drive turbines 7 and 8. The turbine 7 drives a fan 9 circulating air from the enclosure to join the main airstream 4 at 14, and the turbine 8 drives compressors 10 and 11 of a refrigeration circuit including the heat exchanger 15, a subcooler 22, a condenser 21 cooled by air or fuel and expansion ...

IMPROVEMENTS IN AND RELATING TO A SINGLE SHAFT FAN COMPRESSOR AND TURBINE ASSEMBLY

... 1,204,734. Air turbine, compressor and fan assembly. UNITED AIRCRAFT CORP. May 13, 1968 [June 2, 1967], No.22514/68. Heading F1G. The invention relates to a compressor and turbine assembly, such as used for supplying air to an aircraft cabin, the assembly comprising a shaft rotatably mounted in a bearing assembly, a fan rotor mounted at one end of the shaft, a compressor rotor mounted at the other end of the shaft, a turbine rotor mounted on the shaft between the fan and compressor rotors, the turbine having an axial outlet adjacent the bearing assembly, the turbine outlet being so disposed that the air discharging from the turbine serves to cool the bearing assembly. In the embodiment shown, a shaft is supported in a bearing assembly 24, an axial flow fan rotor 36 being mounted at one end of the shaft, a centrifugal compressor rotor 6 being mounted at the other end of the shaft, and a radial inward flow turbine rotor 18 being mounted adjacent the compressor rotor. Bleed air is supplied ...

Cold air refrigeration system and turboexpander turbine for this system

Cold air refrigeration system and turbo-expander turbine for this system.

The cold air refrigerating system comprises a cpmpressor(1), a dual-chamber heat exchanger (2), a turboexpander (6)and a refrigerating chamber (3), with a fan(5)and air coler (4)installed therein. The fan (7)is mounted on the same shaft with the turboexpander (6). The front chambers of the heat exchangers (9 and 2), a moisture separator (8)and the second chamber of the heat exchanger (2)are connected. In another embodiment, the system contains a compressor (44)and a turboexpander (49)a dual-chamber heat exchanger (45), a refrigerating chamber (46), with a fan (48)and an air coler (47)installed therein, a dual-chamber evaporation heat exchanger (51)and a moisture separator (50>the front chambers of the evaporation heat exchangers (51 and 45,)the moisture seperator (50), turboexpander (49)an air cooler (47)and the second chamber of the heat exchanger (45)are connected in tandem with an inlet of the compressor (44). A bearing disc (67)of a turbine (66)is embodied with interblade bores (69) ...

Cold air refrigerating system and turboexpander turbine for this system.

Cold air refrigeration system and turboexpander turbine for this system

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIRPLANE AIR CONDITIONING SYSTEM AND PROCEDURE FOR THE OPERATION OF AN AIRPLANE AIR CONDITIONING SYSTEM

KABINENLUFTUND OF HEAT EXCHANGER ROPE AIR INTAKES FOR AIRPLANE CLIMATIC REGULATION PLANTS AND ALLOCATION USE PROCEDURE

COOLING SYSTEM AND - PROCEDURES FOR COOLING DRINKING WATER IN AN AIRPLANE

TEMPERATURE CONTROL OF COMPRESSED AIR SUPPLY

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

AIR CONDITIONING SYSTEM WITH A ELECTRICAL-PROPELLED TURBOCHARGER

Improved cooling system for a commercial aircraft galley

Improved cooling system for a commercial aircraft galley

Транспортное средство с установкой для кондиционирования воздуха

Настоящая полезная модель относится к транспортному средству с установкой для кондиционирования воздуха, с кондиционером (1), который подготавливает кондиционированный воздух для пассажирского салона, с горизонтально расположенным в продольном направлении транспортного средства воздушным каналом (9), с аэродинамически соединённым с выпускным отверстием (3) для приточного воздуха кондиционера (1) и предусмотренным на участке для распределения воздуха воздушного канала (9) устройством (6) для распределения воздуха, которое направляет подготовленный кондиционером (1) приточный воздух в воздушный канал (9) таким образом, что на первом участке (7) воздушного канала первая часть приточного воздуха проводится в первом направлении потока, а на втором участке (8) воздушного канала вторая часть приточного воздуха, которая по своему объёму меньше, чем первая часть приточного воздуха, проводится во втором направлении потока, противоположном первому направлению потока, и с расположенной в зоне устройства (6) для распределения воздуха ниже и вдоль воздушного канала (9) и аэродинамически соединённой с воздушным каналом (9) через расположенные со стороны днища отверстия (10) воздушного канала (9) демпфирующей камерой (11) для приточного воздуха, которая на своей нижней стороне ограничена относительно пассажирского салона посредством воздухопроницаемого внутреннего потолка салона, причём в зоне первого участка (7, 8) воздушного канала расположено отдельное устройство (14) для изменения направления, которое поворачивает часть первого объёма приточного воздуха в противоположном направлении таким образом, что изменившая направление часть первого объёма приточного воздуха проходит на участке (19) демпфирующей камеры для приточного воздуха ниже устройства (6) для распределения воздуха, и вдоль этого участка (19) демпфирующей камеры для приточного воздуха предусмотрено дроссельное устройство, которое осуществлено и расположено таким образом, что выходной объём приточного воздуха через ...

Piston valve with built in filtration

A control valve includes particle and moisture accumulation inhibiting features. The control valve includes a piston that provides for pressure communication to a back cavity through a tortuous path that settles out particle matter carried within the airflow. Moreover, the piston includes drainage openings that direct moisture out of piston and away from the sealing surfaces.

Catalytic alcohol dehydrogenation heat sink for mobile application

A heat sink is used to absorb heat produced by a vehicle. The heat sink uses an endothermic catalytic alcohol dehydrogenation reaction to assist with the absorption of excess heat produced in the electronics of the vehicle. In some embodiments, the alcohol can be pre-heated by absorbing heat from various components of the vehicle. Excess heat from the various components or from the vehicle engine can be used to vaporize the reaction fluids in order to further absorb additional heat. Reaction fluids can also be sent to the vehicle's engine/burner for use as a supplemental fuel.

Ventilation system and aircraft air-conditioning system

A ventilation system ( 10 ) for installation in an aircraft passenger cabin comprises an air supply pipe ( 12 ), which has a plurality of air outlet openings ( 14 ) disposed in a distributed manner along its longitudinal axis (L). An air chamber housing ( 16 ) is connectable to the air supply pipe ( 12 ) at various positions along the longitudinal axis (L) of the air supply pipe, such that air-conditioning air flowing through the air supply pipe ( 12 ) is supplyable, through an air outlet opening provided in the air supply pipe ( 12 ), into the air chamber housing ( 16 ). A connection device ( 34 ) is designed to connect the air chamber housing ( 16 ) to an air supply device ( 36 ) for supplying air-conditioning air into the aircraft passenger cabin.

Liquid-to-air heat exchanger

A liquid-to-air heat exchanger includes an air inlet header, an air outlet header and a core. The air inlet header has an air inlet connection and the air outlet header has an air outlet connection. The core is connected to the air inlet header and the air outlet header and is angled relative to the air inlet connection and the air outlet connection. More particularly, the air inlet connection and air outlet connection do not align in a straight flow path and the core is disposed at an acute angle relative to one of the air inlet connection and the air outlet connection and an obtuse angle relative to the other of the air inlet connection and the air outlet connection.

Air cycle condenser cold inlet heating using internally finned hot bars

An environmental control system (ECS) includes an air cycle machine with an expansion turbine and a condenser having a cold air inlet connected to receive air from the expansion turbine. The condenser has hollow, internally finned hot bars positioned at the cold air inlet to prevent ice formation at the cold air inlet.

COMPRESSOR/TURBINE ARRANGEMENT, AIR CONDITIONING UNIT AND METHOD FOR OPERATING A COMPRESSOR/TURBINE ARRANGEMENT

The invention relates to a compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system comprising a process air supply line which is designed to supply process air generated by a process air source to a compressor. A detection device is designed to detect a characteristic signal for the temperature of the process air flowing through the process air supply line. A turbine is designed to drive the compressor. A cooling device is disposed in a process air line connecting the compressor to the turbine and is designed to cool the process air coming out of the compressor and flowing through the process air line in the direction of the turbine. Downstream of the cooling device a connecting line branches off from the process air line and opens into the process air supply line. A control device is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device. 1. Compressor/turbine arrangement for use in an air conditioning unit of an aircraft air conditioning system , having:a process air supply line which is designed to supply process air generated by a process air source to a compressor,a detection device which is designed to detect a signal characteristic of the temperature of the process air flowing through the process air supply line,a turbine which is designed to drive the compressor,a cooling device which is arranged in a process air line connecting the compressor to the turbine and is designed to cool the process air exiting the compressor and flowing through the process air line in the direction of the turbine,a connecting line which branches off from the process air line downstream of the cooling device and opens into the process air supply line,a control device which is designed to control a process air flow through the connecting line in dependence on the signal detected by the detection device and characteristic of the temperature of the process air ...

AIR EXTRACTOR FROM A COCKPIT OF A CRAFT

A glider comprises a body , a closed cockpit and an air extractor for extracting air from the cockpit. The extractor is mounted on the body in a region of negative pressure relative to general ambient or atmospheric pressure, in use. The extractor comprises a body defining an inlet , which is in airflow communication with the cockpit , an outlet and a flow passage extending between the inlet and the outlet. An airflow conditioning arrangement is mounted in the passage. 1. A craft comprising a body , a closed cockpit and an air extractor for extracting air from the cockpit , the extractor being mounted on the body in a region of negative pressure relative to general ambient or atmospheric pressure , in use; the extractor comprising a body defining an inlet which is in airflow communication with the cockpit , an outlet and a flow passage extending between the inlet and the outlet; and an air-flow conditioning arrangement mounted in the passage.2. A craft as claimed in wherein the craft is a glider.3. A craft as claimed in wherein the glider comprises an elongate fuselage and a lift providing wing comprising a first wing part on one side of the fuselage and a second wing part on an opposite side of the fuselage and wherein the extractor is mounted in an upper region of the fuselage claim 2 , between the first and second wing parts.4. A craft as claimed in any one of to wherein the passage is trumpet shaped with the inlet in a region thereof having a larger cross sectional area and wherein the passage converges towards a throat.5. A craft as claimed in wherein the flow conditioning arrangement is provided downstream of the throat.6. A craft as claimed in any one of to wherein the flow conditioning arrangement comprises at least one deflector element having a head and a tail.7. A craft as claimed in wherein more than one deflector element are provided and wherein the deflector elements are mounted parallel to one another .8. A craft as claimed in any one of and wherein ...

SYSTEM AND METHOD FOR COOLING AND/OR HEATING AIRCRAFT DEVICES

A system for cooling and/or heating aircraft devices to be cooled and/or heated includes a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated, a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated, a cooling and/or heating energy supply apparatus adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated, a control device adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system. 1. System for cooling and/or heating aircraft devices to be cooled and/or heated , comprising:a first individual cooling and/or heating system associated with a first aircraft device to be cooled and/or heated;a second individual cooling and/or heating system associated with a second aircraft device to be cooled and/or heated;a cooling and/or heating energy supply apparatus which is adapted to supply cooling and/or heating energy generated by the first and/or the second individual cooling and/or heating system to the first and/or the second aircraft device to be cooled and/or heated; anda control device which is adapted to receive and process signals characteristic of the cooling and/or heating requirements of the first and/or the second aircraft device to be cooled and/or heated and of the load condition of the first and/or the second individual cooling and/or heating system, and which is further adapted to control, on the basis of said signals, the operation of the first and/or the second individual cooling and/or heating system and/or the supply of cooling and/or heating energy generated by the first and/or the ...

Integrated air-cycle refrigeration and power generation system

An integrated power and refrigeration system is disclosed that includes a first subsystem configured to provide cooling air using a reverse-Brayton cycle using compressed air and a second subsystem configured to provide power by accepting a first portion of the compressed air from the first subsystem, heating the accepted first portion of the compressed air to form hot compressed air, and using the hot compressed air to drive a turbine that is coupled to a power generator.

PASSENGER SERVICE MODULE AND PASSENGER SERVICE SYSTEM

A passenger service module () comprises a fitting element (), an individual ventilation arrangement () connected to the fitting element () and having at least one air nozzle (), a lighting arrangement () connected to the fitting element () and having at least one reading lamp (), and an operating element () connected to the fitting element (). The operating element () comprises a touch panel () having at least one input field () for individually controlling the operation of the air nozzle () and/or of the reading lamp (). 1. Passenger service module having:a fitting element,an individual ventilation arrangement connected to the fitting element and comprising at least one air nozzle,a lighting arrangement connected to the fitting element and comprising at least one reading lamp, andan operating element connected to the fitting element, the operating element comprising a touch panel having at least one input field for individually controlling the operation of at least one of the air nozzle and the reading lamp.2. Passenger service module according to claim 1 ,wherein at least one of the individual ventilation arrangement and the lighting arrangement is arranged in a housing connected to the fitting element, the housing preferably comprising a cover plate which closes the housing in the region of a surface of the housing that faces the fitting element.3. Passenger service module according to claim 1 ,wherein the fitting element comprises an individual air duct section, which is connectable to an individual air supply line of an individual ventilation system, and a carrier section for connecting the fitting element to at least one of the individual ventilation arrangement, the lighting arrangement and the operating element.4. Passenger service module according to claim 3 ,wherein a first end of the individual air duct section of the fitting element is connected to the individual ventilation arrangement by way of a flexible connecting element, the flexible connecting ...

MIXING DEVICE FOR AN AIRCRAFT AIR CONDITIONING SYSTEM

A mixing device for an aircraft air conditioning system includes a plurality of cold-air supply lines, which are devised to supply cold air to the mixing device. A plurality of warm-air supply lines is further provided, which are devised to supply warm air to the mixing device. A first premixing chamber is connected to the cold-air supply lines and devised to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber. A second premixing chamber is connected to the warm-air supply lines and devised to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber. Finally, a main mixing chamber is connected to the first and the second premixing chambers and devised to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber. 1. Mixing device for an aircraft air conditioning system , comprising:a plurality of cold-air supply lines which are adapted to supply cold air to the mixing device,a plurality of warm-air supply lines, which are adapted to supply warm air to the mixing device,a first premixing chamber, which is connected to the cold supply air lines and adapted to mix the cold air that is fed through the cold-air supply lines into the first premixing chamber,a second premixing chamber which is connected to the warm-air supply lines and adapted to mix the warm air that is fed through the warm-air supply lines into the second premixing chamber, anda main mixing chamber, which is connected to the first and the second premixing chamber and adapted to mix the cold air premixed in the first premixing chamber with the warm air premixed in the second premixing chamber. This application is entitled to and claims the benefit of German Application No. DE 10 2010 014 355.3, German Application No. DE 10 2010 014 354.5, U.S. Provisional Application No. 61/322,571, and U.S. Provisional Application No. 61/322,564, each filed Apr. 9, 2010, the ...

Method and system for controlling an auxiliary power unit

A method for controlling the operation of an auxiliary power unit supplying an aircraft air conditioning system with compressed process air includes determining a heating or cooling requirement of an aircraft region to be air-conditioned, determining a desired value of at least one process air flow parameter in dependence on the determined heating or cooling requirement of the aircraft region to be air-conditioned, controlling the operation of the auxiliary power unit in dependence on the determined process air flow parameter desired value, acquiring an actual value of the at least one process air flow parameter, comparing the process air flow parameter actual value with the process air flow parameter desired value and controlling the operation of the auxiliary power unit in dependence on the result of the comparison of the process air flow parameter actual value with the process air flow parameter desired value.

METHOD FOR OPTIMIZING THE OVERALL ENERGY EFFICIENCY OF AN AIRCRAFT, AND MAIN POWER PACKAGE FOR IMPLEMENTING SAME

A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraft including, in an environment near the cabin, at least one main power-generating engine, sized to serve as a single pneumatic energy-generating source for the cabin and as an at most partial propulsive, hydraulic, and/or electric energy-generating source for the rest of the aircraft. The method minimizes power differential between a nominal point of the power sources when the sources are operating, and a sizing point of non-propulsive energy contributions of the sources when the main engine has failed, by equally dividing power contributions of the main engines and the main power generator under nominal operating conditions and in an event of failure of a main engine. 115-. (canceled)16. A method for optimizing overall efficiency of energy supplied aboard an aircraft , the energy being propulsive or non-propulsive , the aircraft including a passenger cabin with regulated air flow , and power sources including main engines , the method comprising:providing, in an environment located near the cabin, at least one main engine-type power-generating means sized to serve as a single other pneumatic energy-generating source for the cabin and at most partly as an other propulsive, hydraulic, and/or electric energy-generating source for a rest of the aircraft; andminimizing a power difference between a nominal point of the power sources when the power sources are functioning and a sizing point of non-propulsive energy contributions of the power sources in a situation of failure of a main engine, by equally dividing power contributions of the main engines and main power-generating means under nominal operating conditions and in event of the failure of a main engine.17. A main power unit for implementing the optimizing method according to in an ...

Catalyst Systems And Methods For Treating Aircraft Cabin Air

Air treatment catalyst systems and methods for treating the air in the aircraft cabin environment are provided. The catalyst system and method remove ozone, volatile organic compounds, NOx and other pollutants. The catalyst system used to treat the cabin air comprises a plurality of discrete substrates having an ozone abatement catalyst loaded thereon and arranged in a stacked configuration between a source of the air stream and the passenger cabin, the at least the first two substrates adjacent the source of the air stream comprise an iron-based alloy. 1. A catalyst system for treating ozone in an air stream entering a passenger cabin of an aircraft , comprising a plurality of serially arranged , discrete substrates having an ozone abatement catalyst loaded thereon and arranged in a stacked configuration between a source of the air stream and the passenger cabin , at least the first two substrates adjacent the air stream comprising an iron-based alloy.2. The catalyst system of claim 1 , wherein each substrate comprises a honeycomb.3. The catalyst system of claim 2 , wherein at least the first two substrates comprise an iron-chromium alloy.4. The catalyst system of claim 3 , wherein the iron-chromium alloy comprises iron in the range of about 60 weight % to about 80.0 weight % claim 3 , chromium in the range of about 15 weight % to about 30 weight % claim 3 , aluminum in the range of about 2 weight % to about 10 weight % claim 3 , and lanthanum and cerium combined in an amount of less than about 1 weight %.5. The catalyst system of claim 4 , wherein the iron-chromium alloy comprises iron in the range of about 70 weight % to about 80 weight % claim 4 , chromium in the range of about 20 weight % to about 25 weight % claim 4 , aluminum in the range of about 4 weight % to about 8 weight % claim 4 , and lanthanum and cerium combined in an amount of less than about 0.5 weight %.6. The catalyst system of claim 3 , wherein the iron-chromium alloy comprises iron in the range ...

RAM AIR CHANNEL ARRANGEMENT AND AIRCRAFT AIR CONDITIONING SYSTEM

A ram air channel arrangement includes a ram air channel adapted to be flown through with ram air, a heat exchanger disposed in the ram air channel and including a ram air inlet for feeding the ram air flowing through the ram air channel into the heat exchanger and a ram air outlet for removing the ram air from the heat exchanger, and at least one flow control device having a cross section widening in the direction of the ram air inlet and positioned in the ram air channel upstream of the ram air inlet such that it guides the ram air flowing through the ram air channel in the direction of the ram air inlet and/or and at least one flow to control device having a cross section widening in the direction of the ram air outlet and positioned in the ram air channel downstream. 1. Ram air channel arrangement comprising:a ram air channel adapted to be flown through with ram air;a heat exchanger disposed in the ram air channel and including a ram air inlet for feeding the ram air flowing through the ram air channel into the heat exchanger and a ram air outlet for removing the ram air from the heat exchanger; andat least one first flow control device positioned in the ram air channel upstream of the ram air inlet of the heat exchanger in such a way that it guides the ram air flowing through the ram air channel in the direction of the ram air inlet of the heat exchanger and has a cross section widening in a direction of the ram air inlet of the heat exchanger.2. The ram air channel arrangement according to claim 1 , further comprising at least one second flow control device positioned in the ram air channel downstream of the ram air outlet of the heat exchanger in such a way that it guides the ram air flowing through the ram air outlet of the heat exchanger through the ram air channel downstream of the heat exchanger and has a cross section widening in a direction of the ram air outlet of the heat exchanger.3. The ram air channel arrangement according to claim 2 , wherein the ...

Reliable cooling system for operation with a two-phase refrigerant

A cooling system, in particular for use on board an aircraft, includes a first cooling circuit allowing circulation of a two-phase refrigerant therethrough, a first evaporator disposed in the first cooling circuit, a first condenser disposed in the first cooling circuit, and a first heat sink adapted to provide cooling energy to the first condenser. The cooling system further includes a second cooling circuit allowing circulation of a two-phase refrigerant therethrough, a second evaporator disposed in the second cooling circuit, a second condenser disposed in the second cooling circuit, a second heat sink adapted to provide cooling energy to the second condenser, and a cooling energy transfer arrangement which is adapted to transfer cooling energy provided by the first heat sink and/or the first condenser to the second cooling circuit or to transfer cooling energy provided by the second heat sink and/or the second condenser to the first cooling circuit.

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM WITH CONDITIONED HEAT SINK

An air conditioning system for an aircraft includes at least one air conditioning pack which for the purpose of heat dissipation can be connected to at least one cooling air inlet of the aircraft and is designed to cool air and to introduce it at a cabin pressure into a passenger cabin of the aircraft. A separately operable cooling device is designed to cool the ambient air flowing into the cooling air inlet. 1. An air conditioning system for an aircraft , comprising:at least one air conditioning pack connectable to at least one cooling air inlet of the aircraft for heat dissipation and configured to cool air and to introduce it at a cabin pressure into a passenger cabin of the aircraft, andat least one cooling deviceequipped to cool the ambient air flowing into the cooling air inlet, wherein the cooling device is operable separately of the air conditioning pack.2. The air conditioning system of claim 1 , wherein the cooling device is configured as a module accommodatable in a module bay of an aircraft.3. The air conditioning system of claim 1 , wherein the cooling device is configured as an air conditioning system integratable permanently in the aircraft.4. The air conditioning system of claim 3 , wherein the cooling device is configured to provide claim 3 , during the flight of the aircraft claim 3 , the cooling performance used for the cooling of devices within the aircraft.5. The air conditioning system of claim 4 , wherein the cooling device is connectable to an air outlet and an air inlet of a space in the aircraft and comprises a fan for conveying air from the air outlet of the space to the cooling device and from the cooling device to the air inlet of the space.6. The air conditioning system of claim 5 , further comprising a valve arrangement for selectively connecting the cooling air inlet or the air outlet of a space to the separate cooling device.7. The air conditioning system of claim 1 , wherein the cooling device is configured as a heat exchanger ...

METHOD FOR CONTROLLING AN AIRCRAFT AIR CONDITIONING SYSTEM AND AIRCRAFT AIR CONDITIONING SYSTEM

In a method for controlling an aircraft air conditioning system, a heating or cooling demand of an aircraft region to be air conditioned is determined. A volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system is controlled such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized. 1. A method for controlling an aircraft air conditioning system , the method comprising the steps:determining a heating or cooling demand of an aircraft region to be air conditioned, andcontrolling a volume flow of recirculation air discharged from the aircraft region to be air conditioned and a volume flow of compressed air into a mixing chamber of the aircraft air conditioning system such that the heating or cooling demand of the aircraft region to be air conditioned is met, while the volume flow of compressed air into the mixing chamber of the aircraft air conditioning system is minimized.2. The method according to claim 1 , a volume flow of recirculation air discharged from the aircraft region to be air conditioned into the mixing chamber is increased, and', 'the volume flow of compressed air into the mixing chamber is decreased in dependence on the increase of the volume flow of recirculation air into the mixing chamber until the volume flow of compressed air into the mixing chamber has reached the predetermined minimum value., 'wherein, if a heating demand of the aircraft region to be air conditioned is determined and the volume flow of compressed air into the mixing chamber exceeds a predetermined minimum value,'}3. The method according to claim 2 ,wherein the volume flow of compressed air into the mixing chamber corresponds to the predetermined minimum value, when an air conditioning unit of the ...

METHOD AND DEVICE FOR CONTROLLING AN AIRCRAFT AIR CONDITIONING SYSTEM

A method for controlling an aircraft air conditioning system includes the steps of detecting an operating state of an air conditioning unit of the aircraft air conditioning system and controlling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit. 1. A method for controlling an aircraft air conditioning system , having the steps:detecting an operating state of an air conditioning unit of the aircraft air conditioning system, andcontrolling the temperature of a process air mass flow supplied to the air conditioning unit in dependence on the operating state of the air conditioning unit.2. A method according to claim 1 , wherein claim 1 , upon detecting the operating state of the air conditioning unit claim 1 , the operating state of at least one ram air channel flap is determined claim 1 , which controls a flow cross-section of a ram air channel for the supply of ambient air to a heat exchanger unit of the air conditioning unit.3. A method according to claim 1 , wherein claim 1 , upon detecting the operating state of the air conditioning unit claim 1 , the operating state of at least one internal valve of the air conditioning unit is determined which claim 1 , in its open state claim 1 , effects an increase in the temperature of a process air mass flow exiting the air conditioning unit.4. A method according to claim 1 , wherein the temperature of the process air mass flow supplied to the air conditioning unit is altered only if it is determined upon detecting the operating state of the air conditioning unit that the ram air channel flap only frees a minimal flow cross-section of the ram air channel and/or that the internal valve is open.5. A method according claim 1 , wherein the temperature of the process air mass flow supplied to the air conditioning unit is increased if it is determined upon detecting the operating state of the air conditioning unit that the ram air ...

Passenger service system with improved air guidance

A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system, The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (L P ) of the passenger service system.

TURBOPROP-POWERED AIRCRAFT

A method and apparatus are disclosed for a turboprop-powered medium altitude long endurance (MALE) aircraft, having: a heat exchanger with a heat-storage material, for example a heat-storage wax; and an air recirculation path. The heat exchanger can be arranged to cool air recirculating around the air recirculation path which is arranged to provide cooling to the MALE aircraft, for example to an equipment bay. The heat-storage material may be cooled by ground-based cooling apparatus when the aircraft is on the ground and/or by ram air when the aircraft is in flight. The heat-storage material may have a melting point selected so as to be rendered solid during ground-based cooling and/or ram air cooling, and/or selected so as to undergo melting whilst cooling the air recirculating around the air recirculation path. 1. A turboprop-powered medium altitude long endurance aircraft engine , comprising:a heat exchanger having a heat-storage material; andan air recirculation path; whereinthe heat exchanger is configured to cool air recirculating around the air recirculation path; andthe air recirculation path is arranged to allow the recirculating air to provide aircraft cooling air.2. A turboprop-powered medium altitude long endurance aircraft engine according to claim 1 , wherein the heat exchanger is configured such that the heat-storage material will be cooled by ground-based cooling apparatus during aircraft is grounding.3. A turboprop-powered medium altitude long endurance aircraft engine according to claim 1 , wherein the heat exchanger is configured such that the heat-storage material will be cooled by ram air during aircraft flight.4. A turboprop-powered medium altitude long endurance aircraft engine according to claim 2 , wherein the heat-storage material has a melting point selected so as to be rendered solid when cooling is to be performed by the ground-based cooling apparatus and/or by ram air.5. A turboprop-powered medium altitude long endurance aircraft engine ...

COOLING ARRANGEMENT

A cooling arrangement suitable for use in an aircraft includes a cooling energy consumer having a housing which is provided with a cooling fluid inlet for supplying a cooling fluid to the housing and a cooling fluid outlet for discharging the cooling fluid from the housing. The cooling energy consumer is received within a compartment. The compartment is provided with a cooling air inlet for supplying cooling air to the compartment and a cooling air outlet for discharging the cooling air from the compartment. 1. Cooling arrangement suitable for use in an aircraft , the cooling arrangement comprising:a cooling energy consumer having a housing which is provided with a cooling fluid inlet for supplying a cooling fluid to the housing and a cooling fluid outlet for discharging the cooling fluid from the housing, the cooling energy consumer being received within a compartment,wherein the compartment is provided with a cooling air inlet for supplying cooling air to the compartment and a cooling air outlet for discharging the cooling air from the compartment.2. Arrangement according to claim 1 ,further comprising a control unit which is adapted to control the supply of cooling energy to the housing of the cooling energy consumer and the compartment such that, in the event of an unintended leakage of the compartment, the dew point temperature of the air within the compartment is maintained below the surface temperature within the compartment.3. Arrangement according to claim 2 ,wherein the control unit is adapted to control the supply of cooling energy to the housing of the cooling energy consumer and the compartment based on the assumption that an unintended leakage of the compartment leads to a volume flow of 2 to 20 l/s of ambient air from outside the compartment to enter the compartment.4. Arrangement according to claim 2 ,wherein the control unit is adapted to control a volume flow, a speed and/or a direction of flow of cooling air supplied to the compartment such that ...

METHOD FOR CONTROLLING AN AIRCRAFT AIR CONDITIONING SYSTEM DURING MAINTENANCE

In a method for controlling an aircraft air conditioning system, during normal operation of the aircraft, the supply of conditioned air from the aircraft air conditioning system to an aircraft region to be air conditioned is controlled such that the conditioned air is evenly distributed in the aircraft region to be air conditioned. During a predetermined operational phase of the aircraft, the supply of conditioned air from the aircraft air conditioning system to the aircraft region to be air conditioned is controlled such that the conditioned air is distributed only in a selected portion of the aircraft region to be air conditioned.

AIRCRAFT OUTER SKIN HEAT EXCHANGER, AIRCRAFT COOLING SYSTEM AND METHOD FOR OPERATING AN AIRCRAFT OUTER SKIN HEAT EXCHANGER

An aircraft outer skin heat exchanger includes a first cooling air inlet and a first cooling air duct section, in which a first heat carrier fluid duct section is arranged. A cooling air conveying device is configured to convey a cooling air stream in such a way through the first cooling air inlet and the first cooling air duct section that the cooling air stream is subdivided by a first heat carrier fluid duct section, arranged in the first cooling air duct section, into two partial air streams which flow through the first cooling air duct section substantially parallel to one another and in the same direction. 1. Aircraft outer skin heat exchanger having:a first cooling air inlet,a first cooling air duct section,a first heat carrier fluid duct section, arranged in the first cooling air duct section, anda cooling air conveying device which is configured to convey a cooling air stream in such a way through the first cooling air inlet and the first cooling air duct section that the cooling air stream is subdivided by the first heat carrier fluid duct section, arranged in the first cooling air duct section, into two partial cooling air streams which flow through the first cooling air duct section substantially parallel to one another and in the same direction.2. Aircraft outer skin heat exchanger according to claim 1 , further comprising:a second cooling air inlet,a second cooling air duct section, anda second heat carrier fluid duct section, arranged in the second cooling air duct section, the cooling air conveying device being configured to convey a cooling air stream in such a way through the second cooling air inlet and the second cooling air duct section that the cooling air stream is subdivided by the second heat carrier fluid duct section, arranged in the second cooling air duct section, into two partial cooling air streams which flow through the second cooling air duct section substantially parallel to one another and in the same direction.3. Aircraft outer ...

HEAT EXCHANGER INCORPORATED INTO A WALL OF AN AIRCRAFT

An aircraft includes at least one wall delimiting a first zone (I) of the aircraft which is thermally insulated from the outside of the aircraft and a second zone (E) contained within the aircraft which is not thermally insulated with respect to the outside of the aircraft and a heat exchanger inside which a heat transfer fluid circulates, wherein the wall includes at least one duct inside which the heat transfer fluid circulates so as to act as a heat exchanger. 1. An aircraft comprising:at least one wall delimiting a first zone of the aircraft which first zone is thermally insulated from the outside of the aircraft and a second zone contained within the aircraft which second zone is not thermally insulated with respect to the outside of the aircraft; anda first heat exchanger inside which a heat transfer fluid circulates,wherein said at least one wall comprises at least one duct inside which the heat transfer fluid circulates so as to act as a second heat exchanger.2. The aircraft as claimed in claim 1 , wherein the at least one duct is delimited by at least one rib thereby increasing the mechanical strength of the wall.3. The aircraft as claimed in claim 1 , wherein the at least one duct is delimited by the at least one wall claim 1 , one face of which duct is in contact with the heat transfer fluid and the other face of which duct is in contact with the air present in the second zone.4. The aircraft as claimed in claim 1 , wherein the duct projects from the face of the wall in contact with the second zone to increase the surface area for heat exchange between the heat transfer fluid and the air.5. The aircraft as claimed in claim 1 , wherein the at least one wall is a wall or a part of a wall delimiting a landing gear bay.6. The aircraft as claimed in claim 5 , wherein the wall delimiting the landing gear bay comprises claim 5 , on an outer face thereof claim 5 , a plurality of ribs arranged in pairs claim 5 , with a cap for each pair linking the ends of the ...

FLUID TEMPERATURE CONTROL INSTALLATION FOR ROTORCRAFT, ASSOCIATING A SYSTEM FOR COOLING A POWER PLANT WITH A SYSTEM FOR HEATING A CABIN

A fluid temperature control installation for a rotorcraft, the installation comprising a system for cooling a main transmission () and a system for temperature control of the ambient air () of a cabin (). A heat exchanger () is fitted with a bladeless ventilator (). A source air stream () generated by an accessory compressor () driven by the main transmission () passes through the heat exchanger () where it takes heat. The source air stream () is distributed selectively to the bladeless ventilator () to generate a cooling air stream () passing through the heat exchanger (), and/or is distributed to the cabin () after passing through the heat exchanger () in order to heat the ambient air () of the cabin. 1. A fluid temperature control installation for an aircraft , said installation comprising at least one cooling system for cooling at least one member for cooling , and at least one temperature control system for controlling the temperature of the air of a cabin of the aircraft;the cooling system comprising a closed circuit for circulating a fluid for cooling between the member for cooling and at least one heat exchanger fitted with an airflow generator member, the heat exchanger being interposed on the closed circuit by means of an internal circuit for the fluid for cooling, and including a heat exchange structure through which there is passed a stream of cooling air generated by the airflow generator member; andthe air temperature control system comprising regulator means for regulating a stream of heating air admitted to the cabin, and an open circuit conveying a plurality of air streams, the open circuit having a first air circuit for conveying a source air stream generated by a compressor to at least one temperature control device, and a second air circuit for conveying to the cabin said stream of heating air from the temperature control of the source air stream;wherein:said airflow generator member is a bladeless ventilator generating the cooling air stream ...

Aircraft comprising a cooling system for operation with a two-phase refrigerant

An aircraft includes a cooling system having a cooling circuit to circulate a two-phase refrigerant therethrough, an evaporator disposed in a first section of the cooling circuit and having a refrigerant inlet and outlet, a condenser disposed in a second section of the cooling circuit and having a refrigerant inlet and outlet, a first cooling circuit control valve disposed in the cooling circuit between the refrigerant outlet of the evaporator and the refrigerant inlet of the condenser, and a second cooling circuit control valve disposed in the cooling circuit between the refrigerant outlet of the condenser and the refrigerant inlet of the evaporator. The first and the second cooling circuit control valves in their closed state seal the first section of the cooling circuit from the second section of the cooling circuit. The second section of the cooling circuit is installed in an unpressurized region of the aircraft.

Container for an oxygen supply unit, device and system of an arrangement of a number of oxygen supply devices, wherein each oxygen supply unit is stored in a container, method of control of a status and/or change of status of a container

The invention relates to a container for an oxygen supply unit, having a container well at least, wherein a container door can be pivotably joint at a container well's edge, wherein the container is provided with a sensor system, adapted to indicate a status and/or change of status of the door, in particular relative to the well. The invention further relates to a system of an arrangement of a number of oxygen supply devices of claim in a ceiling-panel along an aircrafts cabin, in particular along an aircrafts cabin alley of seats, wherein each oxygen supply unit is stored in a container, in particular in a container according to one of claims to 1. A container for an oxygen supply unit , having a container well at least , wherein a container door can be pivotably joint at a container well's edge , wherein the container is provided with a sensor system , adapted to indicate a status and/or change of status of the door , in particular relative to the well.2. The container of wherein the container door is pivotable about a hinge at the container well's edge and/or the sensor system is provided fully on the door.3. The container of wherein the sensor system is adapted for discriminating between a partial or complete opening of the door.4. The container of wherein the sensor system comprises an opening switch adapted to sense any opening of the door claim 1 , in particular wherein the opening switch is adapted to sense any gap between the door and the well.5. The container of wherein the sensor system comprises a motion sensor adapted to sense a movement of the door claim 1 , in particular relative to the well claim 1 , in particular the motion sensor is formed as an acceleration sensor claim 1 , in particular a three-axis acceleration sensor.6. The container of wherein the sensor system is adapted to sense any status and/or change of status of the door claim 1 , in particular relative to the well claim 1 , in a region distant from the pivotable joint upon pivoting the ...

AIRCRAFT HUMIDIFIER

An aircraft humidifier is engineered as a stand-alone, fully integrated aircraft humidifier that is suitable for providing uniform, non-wetting humidified air disbursed by the aircraft humidifier into ambient air to increase the relative humidity in low humidity environments such as aircraft interiors, including cockpits, cabins, crew rests, cargo holds, and lavatories as well as any other enclosed areas. 1. An aircraft humidifier comprising:a water filtration system that is suitable to produce filtered water without freezing, the water filtration system operating by static water pressure from an aircraft and including stages selected from a group consisting essentially of reverse osmosis and deionization; anda duct that is capable of receiving atomized water droplets formed from the filtered water and compressed air to communicate the atomized water droplets to ambient air, the duct including a mouth, throat, neck, and a mix joint to receive the atomized water droplets, which together communicate the atomized water droplets to a chute, C-joint, and canal, which together in turn communicate the atomized water droplets to the ambient air through a posterior air outlet while evaporating remaining atomized water droplets inside the duct.2. The aircraft humidifier of claim 1 , wherein the duct is selected from a group consisting essentially of incorporating corrugated internal surfaces to agitate the evaporation of atomized water droplets claim 1 , incorporating a spiral curvilinear passage in its internal surfaces claim 1 , incorporating the spiral curvilinear passage that is suitably an expanding spiral claim 1 , incorporating the spiral curvilinear passage that is suitably a constant area spiral claim 1 , incorporating variable side walls in its internal surfaces to minimize the rate of outflow claim 1 , and incorporating variable side walls in its internal surfaces to maximize the rate of outflow.3. The aircraft humidifier of claim 1 , wherein the duct further ...

AIRCRAFT THERMAL CONTROL SYSTEM AND METHOD OF OPERATING AN AIRCRAFT THERMAL CONTROL SYSTEM

An aircraft thermal control system includes a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit. The aircraft thermal control system further includes a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, and a heating circuit which is thermally coupled to the condenser of the thermal control unit. 1. Aircraft thermal control system comprising:a thermal control unit including an internal circuit, an evaporator and a condenser, the evaporator and the condenser being disposed in the internal circuit,a cooling circuit which is thermally coupled to the evaporator of the thermal control unit, anda heating circuit which is thermally coupled to the condenser of the thermal control unit.2. System according to claim 1 ,{'sub': '2', 'wherein the thermal control unit is adapted for operation with COas a refrigerant circulating in the internal circuit.'}3. System according to claim 1 ,wherein a coolant supply line of the cooling circuit which exits the thermal control unit comprises a first line branch thermally connected to a first cooling energy consumer and a second line branch thermally connected to a second cooling energy consumer, wherein a control valve is adapted to control a flow of coolant from the thermal control unit to the first and the second cooling energy consumer.4. System according to claim 1 ,wherein a heating medium supply line of the heating circuit which exits the thermal control unit comprises a first line branch thermally connected to a first heating energy consumer and a second line branch thermally connected to a second heating energy consumer, wherein a control valve is adapted to control a flow of heating medium from the thermal control unit to the first and the second heating energy consumer.5. System according to claim 3 ,wherein the first or the second cooling energy consumer is the aircraft environment, and ...

SYSTEM AND METHOD FOR COOLING A HOVER-CAPABLE AIRCRAFT TRANSMISSION

A system for cooling a transmission of a hover-capable aircraft, the system having: a stator; a heat exchanger connectable thermally to the transmission; a fan for creating a current of a first heat-carrying fluid from the heat exchanger to the fan itself, to remove heat from the heat exchanger; a rotary member, which rotates about an axis to rotate an impeller of the fan about the axis; and a bearing supporting the rotary member for rotation about the axis; the system also having cooling means for cooling the bearing, and in turn having conducting means for conducting a current of a second heat-carrying fluid along a path from an outside environment, external to the bearing, to and to cool the bearing itself. 1761) A system () for cooling a transmission () of a hover-capable aircraft () , the system comprising:{'b': '3', 'a stator ();'}{'b': 8', '6, 'a heat exchanger () connectable thermally to said transmission ();'}{'b': 9', '8', '9', '8, 'a fan () for creating a current (P) of a first heat-carrying fluid from said heat exchanger () to the fan () itself, to remove heat from said heat exchanger ();'}{'b': 10', '20', '9, 'i': 'a', 'a rotary member (), which rotates about an axis (A) to rotate an impeller () of said fan () about said axis (A); and'}{'b': 16', '10', '3, 'a bearing () supporting said rotary member () for rotation about said axis (A) and with respect to said stator ();'}{'b': 16', '40', '42', '41', '30', '29', '50', '16', '16', '16, 'the system being characterized by comprising cooling means for cooling said bearing (); said cooling means comprising conducting means (; , , , ) for conducting a current (Q) of a second heat-carrying fluid along a path from an outside environment (), external to said bearing (), to said bearing () itself, so as to cool the bearing ().'}24042413029) A system as claimed in claim 1 , characterized in that said conducting means (; claim 1 , claim 1 , claim 1 , ) comprise{'b': 41', '10', '50, 'a first cavity () defined by said ...

CABIN AIR SENSOR FOR OZONE DETECTION

A method of measuring a gas concentration is described. The method comprises illuminating, with a light source, a volume of space that includes a gas and measuring, with a detector, a first illumination level of the volume of space. The method further comprises determining, via a processor, a gas concentration in the volume of space based on the measured first illumination level, where the volume of space is configured to be in fluid communication with a gas recirculation flow path including a catalyst, the catalyst configured to substantially remove the gas from the volume of space. 1. A method of measuring a gas concentration , the method comprising:illuminating, with a light source, a volume of space that includes a gas;measuring, with a detector, a first illumination level of the volume of space; anddetermining, via a processor, a gas concentration in the volume of space based on the measured first illumination level,wherein the volume of space is configured to be in fluid communication with a gas recirculation flow path including a catalyst, the catalyst configured to substantially remove the gas from the volume of space.2. The method of claim 1 , further comprising:removing, via a catalyst, the gas from the volume of space;measuring, with the detector, a second illumination level of the volume of space with the gas removed from the volume of space; anddetermining, via the processor, the gas concentration in the volume of space based on a comparison of the second illumination level of the volume and the first illumination level of the volume.3. The method of claim 1 , wherein the gas is ozone.4. The method of claim 1 , wherein the first illumination level comprises ultra-violet (UV) light and the light source comprises a UV light emitting diode (LED).5. The method of claim 1 , wherein the volume of space is defined by a gas housing configured constrain the gas to flow through the volume of space.6. The method of claim 5 , wherein removing the gas from the ...

AIRCRAFT INSTALLATION FOR SUPPLYING PRESSURIZED AIR

An aircraft installation of a pneumatic system of an aircraft with different compressed air sources for supplying pressurized air to air consumer equipment. Either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition, for instance the flight altitude or specific flight phases. Also, a turbofan engine, and a method for supplying compressed air to air consumer equipment are disclosed. 1. An aircraft installation for supplying pressurized air to an air consumer equipment of an aircraft , the aircraft installation comprising:a gas turbine engine having a single port located at a low-intermediate compressor stage of such gas turbine engine; at one end in fluid communication with the single port of the gas turbine engine, and', 'at an opposite end in fluid communication with the air consumer equipment;, 'a bleed duct,'}a cooling duct comprising an inlet by which cooling air enters into the cooling duct, and an outlet;a branch duct in fluid communication with the bleed duct and configured to divert a portion of bleed air from the bleed duct into the outlet of the cooling duct; and the intake is in fluid communication with the outlet of the cooling duct after the joining with the branch duct, and', 'the outlet is in fluid communication with an opposite end of the bleed duct which is communicated with the air consumer equipment., 'an electrical compressor with an intake and an outlet, so that'}2. The aircraft installation according to claim 1 , wherein the inlet of the cooling duct is an air scoop arranged so as to substantially face the incoming cooling air entering into the cooling duct.3. The aircraft installation according to claim 1 , wherein the inlet of the cooling duct is an air scoop arranged so as to be angled relative to the incoming cooling air.4. The aircraft installation according to claim 1 , wherein the intake of the electrical compressor is connected ...

AIR MANAGEMENT SYSTEM

An air management system with a set of compressed air sources for supplying pressurized air to air consumer equipment. In particular, either an air bleed system, electrical compressors, or a combination thereof may perform such supplying of compressed air depending on the aircraft operation condition. 1. An air management system of an aircraft for supplying pressurized air to at least one air consumer , the air management system comprising:the at least one air consumer;at least one air source;at least one gas turbine engine having a single port located at a low-intermediate compressor stage of the gas turbine engine;an air bleed system in fluid communication with the at least one gas turbine engine via the single port of the gas turbine engine, the air bleed system being configured to supply compressed air to the at least one air consumer;at least one electrical compressor in fluid communication with the air source, the at least one electrical compressor being configured to supply compressed air to the at least one air consumer; anda controller configured to receive an input relative to an aircraft operation condition and selectively operate at least one of the air bleed system and the at least one electrical compressor based on the received input.2. The air management system according to claim 1 , wherein the at least one air consumer of the air management system is at least one of the following:an environmental control system;a fuel tank inerting system;a wing anti-ice system;an engine starting system;a water and waste system; andhydraulic reservoirs pressurization.3. An air management system according to claim 2 , wherein the environmental control system comprises a vapor cycle machine configured to be operated by at least one of the air bleed system and the at least one electrical compressor.4. The air management system according to claim 2 , wherein the wing anti-ice system is electrical.5. The air management system according to claim 1 , wherein the air bleed ...

ENVIRONMENTAL CONTROL SYSTEM OF AN AIRCRAFT

An environmental control system for providing a conditioned medium to one or more loads of an aircraft includes a compressing device including a compressor and a turbine operably coupled to the compressor. The turbine is arranged downstream from the compressor relative to a flow of first medium. At least one power turbine is operably coupled to the compressor. The at least one power turbine is configured to receive a flow of a second medium, and the flow of second medium includes a cabin discharge air. 1. An environmental control system for providing a conditioned medium to one or more loads of an aircraft comprising: a compressor;', 'a turbine operably coupled to the compressor, the turbine being arranged downstream from the compressor relative to a flow of first medium; and', 'at least one power turbine operably coupled to the compressor, wherein the at least one power turbine is configured to receive a flow of a second medium, and the flow of second medium includes a cabin discharge air., 'a compressing device including2. The environmental control system of claim 1 , wherein only the first medium is provided to the one or more loads of the aircraft.3. The environmental control system of claim 1 , wherein the first medium is fresh outside air.4. The environmental control system of claim 1 , wherein the at least one power turbine is configured to receive a flow of a third medium.5. The environmental control system of claim 4 , wherein the at least one power turbine includes a single power turbine configured to receive the flow of second medium and the flow of the third medium.6. The environmental control system of claim 5 , wherein the single power turbine includes a first inlet and a second inlet claim 5 , the flow of second medium being provided to the first inlet and the flow of third medium being provided to the second inlet.7. The environmental control system of claim 4 , wherein the at least one power turbine includes a first power turbine configured to ...

SIMULTANEOUS DUAL ENGINE BLEED THERMAL MANAGEMENT SYSTEM

An environmental control system of an aircraft includes at least one heat exchanger and a compression device arranged in fluid communication with the at least one heat exchanger. The compression device includes a plurality of components including a first component and a second component coupled by a shaft. A first bleed port is arranged in fluid communication with the first component and a second bleed port, distinct from the first bleed port, is arranged in fluid communication with the second component. 1. An environmental control system of an aircraft comprising:at least one heat exchanger;a compression device arranged in fluid communication with the at least one heat exchanger, the compression device including a plurality of components including a first component and a second component coupled by a shaft;a first bleed port arranged in fluid communication with the first component; anda second bleed port, distinct from the first bleed port, arranged in fluid communication with the second component.2. The environmental control system of claim 1 , wherein a first medium drawn from the first bleed port has a first pressure and a second medium drawn from the second port has a second pressure claim 1 , the second pressure being higher than the first pressure.3. The environmental control system of claim 1 , wherein at least one of the first bleed port and the second bleed port is in fluid communication with an engine of the aircraft.4. The environmental control system of claim 3 , wherein at least one of the first bleed port and the second bleed port is arranged in fluid communication with a low pressure spool of a compressor of the engine.5. The environmental control system of claim 1 , wherein at least one of the first bleed port and the second bleed port is in fluid communication with an auxiliary power unit of the aircraft.6. The environmental control system of claim 1 , wherein the first component is a compressor and the second component is a turbine.7. The ...

MOISTURE EXTRACTION COMPONENT

A moisture extraction component including: an inlet; an outlet opposite the inlet; an inner surface defining a main flow channel, the main flow channel fluidly connecting the inlet to the outlet; a path on the inner surface configured to direct moisture flow, the path being defined by differences in hydrophobicity on the inner surface using at least one of a hydrophobic surface and a hydrophilic surface. 1. A moisture extraction component , comprising:an inlet;an outlet opposite the inlet;an inner surface defining a main flow channel, the main flow channel fluidly connecting the inlet to the outlet;a path on the inner surface configured to direct moisture flow, the path being defined by differences in hydrophobicity on the inner surface using at least one of a hydrophobic surface and a hydrophilic surface.2. The moisture extraction component of claim 1 , wherein the path is formed by the hydrophilic surface on the inner surface.3. The moisture extraction component of claim 1 , wherein the path is formed by a bare inner surface surrounded by the hydrophobic surface on the inner surface.4. The moisture extraction component of claim 2 , wherein the path is surrounded by the hydrophobic surface on the inner surface.5. The moisture extraction component of claim 1 , further comprising:an exit port fluidly connecting the inner surface and the outer surface, wherein the path is configured to direct moisture flow along the path to the exit port.6. The moisture extraction component of claim 1 , wherein the hydrophobic surface is composed of at least one of rare earth oxides and phosphates.7. The moisture extraction component of claim 1 , wherein the hydrophilic surface is composed of an inorganic oxide.8. The moisture extraction component of claim 1 , wherein the hydrophilic surface is composed of at least one of silica flour claim 1 , alumina claim 1 , and titanium dioxide.9. An air conditioning system for an aircraft claim 1 , the air conditioning system comprising:a ...

METHODOLOGY THAT REGULATES THE SYSTEM COMPONENTS AND OPTIMIZES THE MIXING OF OUTSIDE AIR IN AN ADAPTIVE ENVIRONMENTAL CONTROL SYSTEM

An environment control system (ECS) for controlling an environment in a vehicle includes at least one energy consuming component, means for drawing external air into the environment and a controller, wherein said controller is configured to control the flow rate of the external air being drawn into the environment based on the energy consumption of said at least one energy consuming component. A method of controlling airflow into an environment within a vehicle includes providing an environmental control system that comprises a controller, means for drawing external air into said environment, and at least one energy consuming component and the method further comprising controlling, via the controller, the airflow rate of external air being drawn into the environment, the air flow rate being based on an energy consumption of the at least one energy consuming component. 1. An environment control system (ECS) for controlling an environment in a vehicle , said system comprising at least one energy consuming component , means for drawing external air into the environment anda controller,wherein said controller is configured to control the flow rate of the external air being drawn into the environment based on the energy consumption of said at least one energy consuming component.2. The ECS of wherein{'b': '11', 'said controller is further configured to calculate an optimal air flow rate for said external air () being drawn into said environment based on a change in said energy consumption of said at least one energy consuming component.'}3. The ECS of wherein:said controller is further configured to alter operating conditions for said at least one energy consuming component based on a change in said energy consumption of said at least one energy consuming component and/or a change in said flow rate.5. The ECS of claim 1 , wherein said controller is configured to calculate said air flow rate by further taking into account vehicle operating condition or conditions claim 1 ...

AIRCRAFT FUEL CELL HEAT USAGES

Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. The heat may be used to address condensation within the aircraft. The heat may be used to help evaporate excess water that would otherwise condense in the aircraft skin. The excess water collected may be used to create humidification for cabin air. In other examples, the heat, warmed air, or warmed water may be delivered to other locations or heating systems for beneficial use. 1. A fuel cell by-product use system configured for managing aircraft moisture , comprising:a fuel cell system that creates electricity as a product, and water, heat, and oxygen depleted air as by-products;at least one fluid conduit for delivering the heat generated by the fuel cell to a skin insulation blanket in order to cause evaporation of moisture in the skin insulation blanket; anda collection system for capturing the evaporated moisture and delivering the moisture to an aircraft cabin air distribution system.2. The system of claim 1 , further comprising a system for capturing heat from the fuel cell system and converting the heat to heated air for delivery to the skin insulation blanket system.3. The system of claim 1 , wherein the at least one fluid conduit routes heated air beneath a cabin floor or within cabin walls or both.4. The system of claim 1 , wherein the evaporated moisture is recycled through the aircraft cabin air distribution system via delivery to a humidification system.5. A fuel cell by-product use system configured for managing aircraft heat claim 1 , comprising:a fuel cell system that creates electricity as a product, and water, heat, and oxygen depleted air as by-products;a fluid conduit for delivering the heat generated by the fuel cell to a heating system.6. The system of claim 5 , further comprising a system for controlling the heat ...

THREE WHEEL AND SIMPLE CYCLE AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, at least one dehumidification system arranged in fluid communication with the ram air circuit, a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system. 1. An environmental control system of an aircraft comprising:a ram air circuit including a ram air shell having at least one heat exchanger positioned therein;at least one dehumidification system arranged in fluid communication with the ram air circuit;a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system andan expansion device arranged in fluid communication with the ram air circuit and the at least one dehumidification system.2. The environmental control system of claim 1 , wherein the expansion device is a simple cycle expansion device.3. The environmental control system of claim 1 , wherein the expansion device includes a fan operably coupled to a turbine via a shaft claim 1 , the fan being arranged in fluid communication with the ram air circuit.4. The environmental control system of claim 1 , wherein the compressing device further includes:a turbine configured to provide energy by expanding a first medium; anda compressor configured to receive energy from the first medium being expanded across the turbine, the compressor being configured to compress a second medium.5. The environmental control system of claim 4 , wherein the first medium is bleed air.6. The environmental control system of claim 5 , wherein the bleed air circuit is drawn from at least one of an engine and an auxiliary power unit.7. The environmental control system of claim 4 , wherein the second medium is fresh air.8. The environmental control system of claim 4 ...

THREE WHEEL AND SIMPLE CYCLE AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger. The ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger. A compressing device is arranged in fluid communication with the ram air circuit. 1. An environmental control system of an aircraft comprising:a ram air circuit including a ram air shell having a plurality of heat exchangers positioned therein, the plurality of heat exchangers including a first heat exchanger, a second heat exchanger, and a third heat exchanger, wherein the ram air circuit is configured and arranged so that a first medium received at the first heat exchanger passes through the first heat exchanger and then through the third heat exchanger and so that a second medium received at the second heat exchanger passes through the second heat exchanger; anda compressing device arranged in fluid communication with the ram air circuit.2. The environmental control system of claim 1 , wherein the first heat exchanger claim 1 , the second heat exchanger and the third heat exchanger are coupled together.3. The environmental control system of claim 1 , wherein the first heat exchanger claim 1 , the second heat exchanger and the third heat exchanger are distinct portions within a single unitary body.4. The environmental control system of claim 1 , wherein the first heat exchanger claim 1 , the second heat exchanger and the third heat exchanger are arranged sequentially relative to a flow of ram air.5. The environmental control system of claim 4 , wherein the ram air is configured to interact with the ...

Mixing bleed and ram air using an air cycle machine with two turbines

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

MIXING BLEED AND RAM AIR USING AN AIR CYCLE MACHINE WITH TWO TURBINES

An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine. 1. An air cycle machine for an environmental control system for an aircraft , the air cycle machine comprising:a compressor configured to compress a first medium;a turbine configured to receive second medium;a mixing point downstream of the compressor and downstream of the turbine;a shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.2. The air cycle machine of claim 1 , further comprising the fan on a second shaft.3. The air cycle machine of claim 2 , wherein the fan is located at a first end of the second shaft.4. The air cycle machine of claim 3 , wherein a third turbine is located at a first end of the shaft.5. The air cycle machine of claim 4 , further comprising the fan located at a second end of the shaft.6. The air cycle machine of claim 3 , wherein the second turbine is configured to receive a third medium claim 3 , andwherein the third medium is cabin discharge air.7. The air cycle machine of claim 1 , wherein the first medium comprises fresh air claim 1 , andwherein the second medium comprises bleed air.8. An air conditioning system for an aircraft comprising:a compressor configured to compress a first medium;a turbine configured to receive a second medium;a mixing point downstream of the compressor and downstream of the turbine; anda shaft mechanically coupling the compressor and the turbine;a second turbine mounted on the shaft and configured to expand the first medium; anda fan driven by a motor.9. The air conditioning system of claim 8 , further comprising the fan on a second shaft.10. ...

HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS

An architecture for powering systems on an aircraft has a gas turbine engine including a main compressor, a combustor, and a turbine. The turbine powers the main compressor, and further powers a propulsor. The turbine is operably connected to drive a generator. The generator is connected to store generated power at a battery. The battery is connected to provide power to a motor from the propulsor such that the propulsor can be selectively driven by both the motor and the turbine. A bleed air control system and a tap for selectively tapping compressed air from the main compressor, and a control valve for delivering at least one of the tapped compressed air or a compressed alternative air to bleed systems on an associated aircraft. An electric bleed compressor selectively compresses the compressed alternative air. The electric bleed compressor is powered by the battery. A control for controlling the control valve to selectively deliver at least one of the tapped compressed air and the compressed alternative air to the bleed systems. An aircraft is also disclosed. 1. An architecture for powering systems on an aircraft comprising:a gas turbine engine including a main compressor, a combustor, and a turbine, said turbine powering said main compressor, and further powering a propulsor;said turbine also being operably connected to drive a generator, said generator being connected to store generated power at a battery, said battery being connected to provide power to a motor to power said propulsor such that said propulsor can be selectively driven by both said motor and said turbine;a bleed air control system, and a tap for selectively tapping compressed air from said main compressor, and a control valve for delivering at least one of said tapped compressed air or a compressed alternative air to bleed systems on an associated aircraft; andan electric bleed compressor for selectively compressing the compressed alternative air, said electric bleed compressor powered by said ...

TWO-TURBINE GEARED ENGINE WITH LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM FOR AIRCRAFT

A gas turbine engine assembly includes a fan section delivering air into a main compressor section. The main compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. A pylon supports the gas turbine engine. An environmental control system includes a higher pressure tap at a higher pressure location in the main compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet and a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. The pylon includes a lowermost surface and the higher pressure tap does not extend above a plane including the lowermost surface. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. An environmental control system is also disclosed. 1. A gas turbine engine assembly comprising:a fan section delivering air into a main compressor section, said main compressor section compressing air and delivering air into a combustion section, products of combustion passing from said combustion section over a turbine section to drive said fan section and main compressor sections, wherein a gearbox is driven by said turbine section to drive said fan section;a pylon supporting the gas turbine engine;an environmental control system including a higher pressure tap at a higher pressure location in said main compressor section, and a lower pressure tap at a lower ...

Supply of air to an air-conditioning circuit of an aircraft cabin from its turboprop engine

An aircraft turboprop engine includes at least a low-pressure body and a high-pressure body. The low-pressure body drives a propeller by means of a gearbox. The turboprop engine also includes means for supplying air to an air-conditioning circuit of an aircraft cabin, wherein the supply means has at least one compressor borne by the gearbox and of which the rotor is coupled to the low-pressure body by means of the gearbox.

SYSTEMS, DEVICES AND METHODS FOR REGENERATION OF A SORBENT

An environmental control system is provided. The system includes a sorbent regeneration device. The sorbent regeneration device includes at least one regenerative sorbent material operative to remove gas substances from air. The at least one regenerative sorbent material is operatively coupled to a source of hot air. The sorbent regeneration device further includes at least two bypass valves that are operative to selectively direct some or all of the hot air into the at least one regenerative sorbent material. The environmental control system further includes one or more air quality sensors and a controller operatively connected to the at least two bypass valves and the one or more air quality sensors. The controller is operative to control one or more of the at least two bypass valves in response to air quality determined from the air quality sensors. 1. An environmental control system comprising: at least one regenerative sorbent material operative to remove gas substances from air, the at least one regenerative sorbent material operatively coupled to receive hot air; and', 'at least two bypass valves operative to selectively direct some or all of the hot air to the at least one regenerative sorbent material;, 'a sorbent regeneration device comprisingone or more air quality sensors; and determine an air quality value based on signals from the one or more air quality sensors; and', 'control the at least two bypass valves in response to the air quality value., 'a controller operatively connected to the sorbent regeneration device, and the one or more air quality sensors, the controller operative to2. The environmental control system of claim 1 , wherein the sorbent regeneration device comprises at least two regenerative sorbent materials claim 1 , and wherein the controller is further operative to selectively direct the hot air independently to one of the at least two regenerative sorbent materials.3. The environmental control system of claim 1 , wherein the ...

ANTIMICROBIAL SURFACES FOR FLOW PATH COMPONENTS

According to an aspect, a flow path component includes a flow path component body having a flow surface. The flow path component also includes a plurality of antimicrobial nanoparticles embedded in the flow surface and at least partially exposed external to the flow surface to provide an antimicrobial surface. 1. A flow path component , comprising:a flow path component body comprising a flow surface; anda plurality of antimicrobial nanoparticles embedded in the flow surface and at least partially exposed external to the flow surface.2. The flow path component of claim 1 , wherein the antimicrobial nanoparticles comprise one or more of silver and silver oxide nanoparticles.3. The flow path component of claim 1 , wherein the flow path component body is composed of a non-metallic material.4. The flow path component of claim 1 , wherein the flow surface comprises a hydrophobic surface containing the antimicrobial nanoparticles.5. The flow path component of claim 1 , wherein the antimicrobial nanoparticles form a nanoscale texturing on the flow surface.6. The flow path component of claim 1 , wherein the antimicrobial nanoparticles embedded in the flow surface are bonded to the flow path component body by an adhesive material.7. An air conditioning system for an aircraft claim 1 , the air conditioning system comprising:an air cycle machine; and a flow path component body comprising a flow surface; and', 'a plurality of antimicrobial nanoparticles embedded in the flow surface and at least partially exposed external to the flow surface., 'a heat exchanger operably coupled to the air cycle machine, the heat exchanger comprising at least one flow path component comprising8. The air conditioning system of claim 7 , wherein the antimicrobial nanoparticles comprise one or more of silver and silver oxide nanoparticles.9. The air conditioning system of claim 7 , wherein the flow path component body is composed of a non-metallic material.10. The air conditioning system of claim 7 , ...

AIRCRAFT AIR SUPPLY AND CONTAMINANT DETECTION SYSTEM

An aircraft pressurized air system and method is disclosed. The system includes a compressor that receives and compresses outside air, and an air cycle machine that receives compressed air from the compressor and directs conditioned air to an aircraft pressurized zone. The system also includes a contaminant sensor disposed along an air flow path between the compressor and the aircraft pressurized zone, comprising an optical guide, a metal organic framework on an exterior surface of the optical guide in operative fluid communication with air from the air flow path, a light source in communication with the optical guide at a first end of the optical guide, and a light detector in communication with the optical guide at a second end of the optical guide. 1. An aircraft pressurized air system , comprising:a compressor that receives and compresses outside air;an air cycle machine that receives compressed air from the compressor and directs conditioned air to an aircraft pressurized zone; anda contaminant sensor disposed along an air flow path between the compressor and the aircraft pressurized zone, comprising an optical guide, a metal organic framework on an exterior surface of the optical guide in operative fluid communication with air from the air flow path, a light source in communication with the optical guide at a first end of the optical guide, and a light detector in communication with the optical guide at a second end of the optical guide.2. The system of claim 1 , wherein the optical guide comprises a fiber optic element including a core comprising an optical material with a first refractive index claim 1 , said metal organic framework on a first exterior surface portion of the core claim 1 , and a cladding optically coupled to a second exterior surface portion of the core claim 1 , said cladding comprising an optical material with a second refractive index lower than the first refractive index and configured to reflect light from the core at an interface ...

AIRCRAFT AIR CONDITIONING SYSTEM AND METHOD OF OPERATING AN AIRCRAFT AIR CONDITIONING SYSTEM

An aircraft air conditioning system comprising an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer. A first compressor is arranged in the ambient air supply line and is configured to compress the ambient air flowing through the ambient air supply line. A bleed air supply line allows a flow of bleed air bled off from an engine or an auxiliary power unit therethrough. A bleed air turbine is driven by the bleed air flowing through the bleed air supply line and is coupled to the first compressor so as to drive the first compressor. 1. An aircraft air conditioning system comprising:an ambient air supply line having a first end connected to an ambient air inlet and a second end connected to a mixer of the aircraft air conditioning system so as to supply ambient air to the mixer,a first compressor arranged in the ambient air supply line and being configured to compress ambient air flowing through the ambient air supply line,a bleed air supply line having a first end connected to an engine or an auxiliary power unit and a second end connected to an aircraft environment, a bleed air turbine driven by bleed air flowing through the bleed air supply line and being coupled to the first compressor so as to drive the first compressor,an ambient air branch line branching off from the ambient air supply line upstream of the first compressor and opening into the ambient air supply line downstream of the first compressor,a second compressor arranged in the ambient air branch line and being configured to compress the ambient air flowing through the ambient air branch line,a cabin exhaust air line allowing a flow of cabin exhaust air therethrough, anda cabin exhaust air turbine driven by the cabin exhaust air flowing through the cabin exhaust air line and being coupled to the second compressor so as to drive the second compressor.2. The ...

Aircraft air conditioning system and method of operating an aircraft air conditioning system

An aircraft air conditioning system comprising an ambient air supply line allowing a flow of ambient air therethrough, an ambient air cooling device to cool the air flowing through the ambient air supply line, and a discharge line connected to the ambient air cooling device and an aircraft cabin. A compressed air supply line allows a flow of compressed air therethrough, a compressed air cooling device is connected to the compressed air supply line to cool the air flowing through the compressed air supply line, and a discharge line is connected to the compressed air cooling device and to the aircraft cabin. A refrigerant circuit allows the flow of a two-phase refrigerant therethrough and converts the two-phase refrigerant from the liquid state into the gaseous state of aggregation and thereafter back again. The refrigerant circuit supplies cooling energy to the ambient air cooling device and the compressed air cooling device. 1. An aircraft air conditioning system comprising:an ambient air supply line allowing a flow of ambient air therethrough,an ambient air cooling device connected to the ambient air supply line and being adapted to cool the ambient air flowing through the ambient air supply line,an ambient air discharge line connected to the ambient air cooling device and being connectable to an aircraft cabin,a compressed air supply line allowing a flow of compressed air therethrough,a compressed air cooling device connected to the compressed air supply line and being adapted to cool the compressed air flowing through the compressed air supply line,a compressed air discharge line connected to the compressed air cooling device and being connectable to the aircraft cabin, anda refrigerating apparatus comprising a refrigerant circuit allowing the flow of a two-phase refrigerant therethrough and being configured to convert the two-phase refrigerant, upon flowing though the refrigerant circuit, from the liquid state of aggregation into the gaseous state of aggregation ...

MAINTENANCE SYSTEMS AND METHODS FOR ECS ELEMENTS

A maintenance system is provided for an environment conditioning element of an environmental control system (ECS) of a vehicle. The system includes a data collection module configured to receive geographical areas of travel for the vehicle over respective periods of time. The data collection module is configured to determine a pollution value and a time value for each of the geographic areas of travel. The system further includes a pollution count module coupled to the data collection module and receiving the pollution values and the time values. The pollution count module is configured to determine a pollution count for the environment conditioning element based on the pollution values and the time values. The system further includes a reporting module coupled to the pollution count module and receiving the pollution count. The reporting module is configured to generate a report for a user that includes the pollution count. 1. A maintenance system for an environment conditioning element of an environmental control system (ECS) of a vehicle , comprising:a data collection module configured to receive geographical areas of travel for the vehicle over respective periods of time, the data collection module configured to determine a pollution value and a time value for each of the geographic areas of travel;a pollution count module coupled to the data collection module and receiving the pollution values and the time values, the pollution count module configured to determine a pollution count for the environment conditioning element based on the pollution values and the time values; anda reporting module coupled to the pollution count module and receiving the pollution count, the reporting module configured to generate a report for a user that includes the pollution count.2. The maintenance system of claim 1 ,wherein the pollution count module is configured to generate a pollution count increment for each of the pollution values and the time values and to generate the ...

INDEPENDENT POWER GENERATION IN AIRCRAFT

A method includes generating thrust at one or more engines of an aircraft. The method includes generating first electricity at a first power unit concurrently with generating second electricity at a second power unit. The first power unit and the second power unit are independent of the one or more engines of the aircraft. The first electricity has a first set of electrical characteristics and the second electricity has a second set of electrical characteristics, where the first set of electrical characteristics is different than the second set of electrical characteristics. 1. A method comprising:generating thrust at one or more engines of an aircraft;generating first electricity at a first power unit that is independent of the one or more engines of the aircraft, the first electricity having a first set of electrical characteristics;concurrently with generating the first electricity, generating second electricity at a second power unit that is independent of the one or more engines of the aircraft, the second electricity having a second set of electrical characteristics, wherein the first set of electrical characteristics is different than the second set of electrical characteristics; andreceiving the first electricity at an environmental control system (ECS) of the aircraft, wherein, during flight, the ECS is electrically and pneumatically isolated from the one or more engines.2. The method of claim 1 , further comprising claim 1 , before generating thrust at the one or more engines of the aircraft claim 1 , starting the one or more engines of the aircraft using the first electricity.3. The method of claim 1 , wherein claim 1 , during flight claim 1 , the first power unit generates the first electricity independent of the one or more engines of the aircraft.4. The method of claim 1 , wherein claim 1 , during flight claim 1 , the second power unit generates the second electricity independent of the one or more engines of the aircraft.5. The method of claim 1 , ...

HIGH-PRESSURE ANNULAR WATER COLLECTOR WITH AXIAL SWIRL VANES FOR AN AIR CYCLE ENVIRONMENTAL CONTROL SYSTEM

An annular water removal system (AWRS) for an air cycle environmental control system (ECS) includes a line replaceable unit (LRU) configured to output air flow, and a water collector coupled to the LRU. The water collector includes an upper portion and a lower portion. The upper portion includes a coalescing unit having a collector inlet to receive the air flow and configured to coalesce moisture from the air flow output from the LRU. The lower portion includes a collection unit in fluid communication with the coalescing unit. The collection unit is configured to collect the moisture coalesced by the coalescing unit. 1. A water collector configured to remove moisture from air flow output from a line replaceable unit (LRU) , the water collector comprising:an upper portion including a coalescing unit having a collector inlet to receive the air flow, and configured to coalesce moisture from the air flow output from the LRU; anda lower portion including a collection unit in fluid communication with the coalescing unit, the collection unit configured to collect the moisture coalesced by the coalescing unit.2. The water collector of claim 1 , wherein the water collector includes a housing extending radially about a center axis to define an annular profile with an opening configured to receive the LRU.3. The water collector of claim 2 , wherein the water collector is configured to wrap entirely around at least a portion of the LRU such that an air outlet of the LRU is in fluid communication with the collector inlet.4. The water collector of claim 2 , wherein the upper portion further includes an outlet flange having a torus profile that defines a collector outlet configured to expel the air exiting the coalescing unit in a direction that is orthogonal to the center axis.5. The water collector of claim 4 , wherein the coalescing unit includes a helical air passage.6. The water collector of claim 5 , wherein the helical passage is defined by an inlet channel extending from ...

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

A compressing device for use in an environmental control system includes at least one turbine configured to provide energy by expanding one or more medium. The one or more mediums provided at an outlet of the at least one turbine form a heat sink within the environmental control system. A compressor is configured to receive energy from the one or more mediums expanded across the at least one turbine. During a first mode of the compressing device, energy derived from a first medium of the one or more mediums is used to compress a second medium at the compressor and during a second mode of the compressing device, energy derived from both the first medium and a third medium of the one or more mediums is used to compress a second medium at the compressor. 1. A compressing device for use in an environmental control system comprising:at least one turbine configured to provide energy by expanding one or more mediums, wherein the one or more mediums provided at an outlet of the at least one turbine form a heat sink within the environmental control system; anda compressor configured to receive energy from the one or more mediums expanded across the at least one turbine, wherein during a first mode of the compressing device, energy derived from a first medium of the one or more mediums is used to compress a second medium at the compressor and during a second mode of the compressing device, energy derived from both the first medium and a third medium of the one or more mediums is used to compress a second medium at the compressor.2. The compressing device of claim 1 , wherein the at least one turbine includes a first turbine configured to receive and extract work from the first medium and a second turbine configured to receive and extract work from the third medium.3. The compressing device of claim 2 , wherein the first medium and the third medium are mixed together downstream from both the first turbine and the second turbine.4. The compressing device of claim 2 , wherein ...

Aircraft environmental control system

An environmental control system of an aircraft includes a plurality of inlets for receiving a plurality of mediums including a first medium, a second medium, and a third medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. At least one compressing device is arranged in in fluid communication with the plurality of inlets and the outlet. The at least one compressing device includes a four-wheel compressing device having a compressor and at least one turbine operably coupled via a shaft. In a first mode of operation, the compressor is driven by the first medium, and in a second mode of operation, the compressor is driven by the third medium.

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein and a divider arranged within the ram air shell to separate the ram air shell into a first region and a second region. The at least one heat exchanger is arranged within both the first region and the second region. A first medium is configured to flow through the first region and a second, distinct medium is configured to flow through the second region. The environmental control system additionally includes a dehumidification system arranged in fluid communication with the ram air circuit and a compression device arranged in fluid communication with the ram air circuit and the dehumidification system. 1. An environmental control system of an aircraft comprising: a ram air shell having at least one heat exchanger positioned therein;', 'a divider arranged within the ram air shell to separate the ram air shell into a first region and a second region, the at least one heat exchanger being arranged within both the first region and the second region, wherein a first medium is configured to flow through the first region and a second, distinct medium is configured to flow through the second region;', 'a dehumidification system arranged in fluid communication with the ram air circuit; and', 'a compression device arranged in fluid communication with the ram air circuit and the dehumidification system, the compression device including a compressor and a turbine., 'a ram air circuit including2. The environmental control system of claim 1 , wherein the at least one heat exchanger includes a first portion arranged within the first region and a second portion arranged within the second region claim 1 , the second portion of the at least one heat exchanger is integrally formed with the first portion.3. The environmental control system of claim 2 , wherein the second portion of the heat exchanger is a condenser of the ...

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

An environmental control system includes a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium and an outlet for delivering a conditioned form of the second medium to at least one load of the aircraft. A ram air circuit includes a ram air shell having at least one heat exchanger positioned therein and a dehumidification system is arranged in fluid communication with the ram air circuit. A compression device is arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a plurality of turbines including a first turbine and a second turbine operably coupled by a shaft. An outlet of the first turbine is directly coupled to an inlet of the second turbine, such that the first medium is provided to the first turbine and the second turbine in series. 1. An environmental control system of an aircraft comprising:a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium;an outlet for delivering a conditioned form of the second medium to at least one load of the aircraft;a ram air circuit including a ram air shell having at least one heat exchanger positioned therein;a dehumidification system arranged in fluid communication with the ram air circuit; anda compression device arranged in fluid communication with the ram air circuit and the dehumidification system, the compression device including a compressor and a plurality of turbines including a first turbine and a second turbine operably coupled by a shaft, wherein an outlet of the first turbine is directly coupled to an inlet of the second turbine, such that the first medium is provided to the first turbine and the second turbine in series.2. The environmental control system of claim 1 , wherein the compressor is operable to receive a second medium claim 1 , and the compressor is driven by work extracted from the first medium within the first turbine ...

ENVIRONMENTAL CONTROL SYSTEM PACK

An environmental control system is provided including a ram air circuit having a ram air duct and at least one heat exchanger arranged within the ram air duct. The ram air duct is curved about a ram axis. A compression device includes a compressor and at least one turbine operably coupled by a shaft rotatable about a shaft axis. The ram axis is arranged coaxially with the shaft axis. 1. An environmental control system comprising:a ram air circuit including a ram air duct and at least one heat exchanger arranged within the ram air duct, the ram air duct being curved about a ram axis; anda compression device including a compressor and at least one turbine operably coupled by a shaft rotatable about a shaft axis;wherein the ram axis is arranged coaxially with the shaft axis.2. The environmental control system of claim 1 , wherein the ram air duct has a scroll-shaped outer wall that is curved about the ram axis.3. The environmental control system of claim 1 , wherein a portion of the ram air duct is directly connected to the compression device.4. The environmental control system of claim 1 , wherein the ram air circuit further comprises a diffuser/ejector arranged within the ram air duct claim 1 , wherein a plenum is defined between an exterior of the diffuser/ejector and an interior of the ram air duct and the at least one heat exchanger is arranged within the plenum.5. The environmental control system of claim 4 , wherein the diffuser/ejector extends external to the ram air duct.6. The environmental control system of claim 4 , wherein the at least one heat exchanger extends external to the ram air duct.7. The environmental control system of claim 4 , wherein a diameter of the diffuser/ejector increases along a fluid flow path defined by an interior of the ejector.8. The environmental control system of claim 4 , wherein the at least one heat exchanger is mounted concentrically about at least a portion of the ejector.9. The environmental control system of claim 4 , ...

Aircraft environmental control system

An environmental control system of an aircraft including a plurality of inlets for receiving a plurality of mediums including a first medium, a second medium, and a third medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. The environmental control system additionally includes a first compressing device and a second compressing device. The second compressing device is arranged in fluid communication with the first compressing device and the outlet. An inlet of the second compressing device is directly connected to an outlet of the first compressing device, and the first compressing device is driven by energy extracted from the first medium. The first medium is a flow of bleed air.

AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM

An air cycle machine for an environmental control system for an aircraft includes at least one turbine configured to receive and extract work from a first medium and a third medium. A compressor is configured to compress a second medium and a shaft mechanically couples the at least one turbine and the compressor. A mixing point is located downstream of at least one turbine. A mixture of the first medium and the third medium generated at the mixing point is provided to another component of the environmental control system. 1. An air cycle machine for an environmental control system for an aircraft , the air cycle machine comprising:at least one turbine configured to receive and extract work from a first medium and a third medium;a compressor configured to compress a second medium;a shaft mechanically coupling the at least one turbine and the compressor; anda mixing point located downstream of at least one turbine, wherein a mixture of the first medium and the third medium generated at the mixing point is provided to another component of the environmental control system.2. The air cycle machine of claim 1 , wherein the at least one turbine includes a first turbine configured to receive and extract work from the first medium and a second turbine configured to receive and extract work from the third medium.3. The air cycle machine of claim 2 , wherein the mixing point is located downstream of the first turbine and the second turbine.4. The air cycle machine of claim 2 , wherein the first turbine is positioned adjacent a first end of the shaft and the second turbine is positioned adjacent a second end of the shaft.5. The air cycle machine of claim 2 , wherein the first turbine is positioned adjacent a first end of the shaft and the compressor is positioned adjacent a second end of the shaft.6. The air cycle machine of claim 2 , wherein the mixing point is located upstream of the second turbine.7. The air cycle machine of claim 6 , wherein the first turbine and the second ...

Aircraft environmental control system

An environmental control system of an aircraft includes a plurality of inlets for receiving a plurality of mediums including a first medium and a second medium and an outlet for delivering a conditioned flow of the second medium to one or more loads of the aircraft. A ram air circuit includes a ram air shell having at least one heat exchanger positioned therein. A compressing device is arranged in fluid communication with the ram air circuit and the outlet. The compressing device including a first compressor, a second compressor, and at least one turbine operably coupled via a shaft. The first compressor and the second compressor are arranged in parallel with respect to a flow of the second medium and the first medium is used as a heat sink by another component within the environmental control system.

RAF BIT FOR SURGE DETECTION

A ram air fan (RAF) assembly is provided and includes a ram air inlet, a heat exchanger disposed in the ram air inlet, an RAF disposed in the ram air inlet to drive airflow through the heat exchanger, a sensor disposed in the ram air inlet proximate to the RAF and a controller. The controller is operably coupled to the RAF and the sensor and is configured to drive rotations of the RAF to achieve a target RAF rotational speed in accordance with a determination that a reading generated by the sensor is indicative of a surge event. 1. A ram air fan (RAF) assembly , comprising:a ram air inlet;a heat exchanger disposed in the ram air inlet;an RAF disposed in the ram air inlet to drive airflow through the heat exchanger;a sensor disposed in the ram air inlet proximate to the RAF; anda controller operably coupled to the RAF and the sensor, the controller being configured to drive rotations of the RAF to achieve a target RAF rotational speed in accordance with a determination that a reading generated by the sensor is indicative of a surge event.2. The RAF assembly according to claim 1 , wherein the heat exchanger comprises a primary heat exchanger and a secondary heat exchanger in series.3. The RAF assembly according to claim 1 , wherein the RAF is downstream from the heat exchanger.4. The RAF assembly according to claim 3 , wherein the sensor is downstream from the RAF.5. The RAF assembly according to claim 1 , wherein the sensor comprises a pressure sensor.6. The RAF assembly according to claim 1 , wherein the controller comprises:an electric motor configured to drive the rotations of the RAF;a motor controller configured to control an operation of the electric motor; anda pack controller configured to determine a current RAF rotational speed, to register that the reading generated by the sensor is indicative of a surge event and to instruct the motor controller to control the operation of the electric motor accordingly.7. The RAF assembly according to claim 1 , wherein ...

System, Methods, and Apparatus for Air Flow Handling in an Aircraft Monument

In an illustrative embodiment, an aircraft galley ducting assembly provides airflow to at least one compartment of an aircraft galley monument. The ducting assembly may include a supply air duct that provides a supply airflow path to a compartment that includes an inlet port mounted to a compartment surface. A return air duct may provide an exit airflow path for return air that has circulated throughout the compartment and includes an outlet port mounted to the compartment surface. An airflow adjustment apparatus with an airflow adjustment surface is positioned within the supply airflow path of the supply air duct or the exit airflow path of the return air duct to cause a modification of airflow properties for air passing across or through the airflow adjustment surface. 1. A ducting assembly for providing airflow to at least one compartment of an aircraft galley monument , the ducting assembly comprising:a supply air duct configured to provide a supply airflow path from an external air system to a first compartment of the at least one compartment, the supply air duct including an inlet port mounted to a surface of the compartment to provide an inlet path for air flowing from the supply air duct to the compartment;a return air duct configured to provide an exit airflow path to the external air system for return air that has circulated throughout the compartment, the return air duct including an outlet port mounted to a surface of the compartment to provide an outlet path for the return air from the compartment to the return air duct; andan airflow adjustment apparatus including an airflow adjustment surface disposed within at least one of the supply airflow path of the supply air duct and the exit airflow path of the return air duct, the airflow adjustment surface configured to cause a modification of airflow properties for air flowing across or through the airflow adjustment surface.2. The ducting assembly of claim 1 , wherein the airflow properties include at ...

Modular Aircraft Galley Systems, Apparatus and Methods for Configuration

In a preferred embodiment, a modular galley monument for an aircraft cabin includes a first side panel, a second side panel, and an upper surface connecting the first side panel and the second side panel. The modular galley monument may include dividers partitioning the monument into a number of compartments. The monument may include an upper monument portion and a lower monument portion connected at a periphery via a seal allowing for vertical deflection between the first monument portion and the second monument portion of at least one inch while maintaining contact with both. The monument may include an integrated heating appliance for a compartment, including an insulation shell, a heated compartment positioned within the insulation shell, an electrical heating unit disposed within the insulation shell and configured to provide heat energy to the heated compartment. and a door assembly rotatably connected about an opening of the heated compartment.

BLEED AIR HEAT EJECTORS

A bleed air heat ejector includes a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing. A dispenser is mounted in the housing between the inlet and the outlet. The dispenser includes an inner chamber configured to receive heated air from a bleed line. The dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air. The apertures of the inner chamber can be angled primary jets, vortex generators can be included, and/or secondary jets can be included to promote mixing of bleed and ambient air. 1. A bleed air heat ejector comprising:a housing defining an inner passage extending in an axial direction from an inlet of the housing to an outlet of the housing, wherein the inlet is configured to channel ambient air into the housing, and wherein the outlet is configured to channel mixed heated and ambient air out of the housing;a dispenser mounted in the housing between the inlet and the outlet, wherein the dispenser includes an inner chamber configured to receive heated air from a bleed line, wherein the dispenser includes a plurality of apertures therein for issuing heated air from the inner chamber into the inner passage of the housing to form a flow of mixed ambient and bleed air; anda plurality of vortex generators mounted in the inner passage downstream of the apertures in the inner chamber, wherein the vortex generators are configured to promote mixing of bleed and ambient air.2. A bleed air heat ejector as recited in claim 1 , wherein the inner passage defines a venturi with a throat claim 1 , wherein the apertures of the inner chamber are directed downstream from the throat of the venturi claim 1 , wherein ...

System, Methods, and Apparatus for Air Flow Handling in an Aircraft Monument

In an illustrative embodiment, an aircraft galley ducting assembly provides airflow to at least one compartment of an aircraft galley monument. The ducting assembly may include a supply air duct that provides a supply airflow path to a compartment that includes an inlet port mounted to a compartment surface. A return air duct may provide an exit airflow path for return air that has circulated throughout the compartment and includes an outlet port mounted to the compartment surface. An airflow adjustment apparatus with an airflow adjustment surface is positioned within the supply airflow path of the supply air duct or the exit airflow path of the return air duct to cause a modification of airflow properties for air passing across or through the airflow adjustment surface. 1. A ducting assembly for providing airflow to at least one compartment of an aircraft galley monument , the ducting assembly comprising:a supply air duct configured to provide a supply airflow path from an external air system to a first compartment of the at least one compartment, the supply air duct including an inlet port mounted to a surface of the compartment to provide an inlet path for air flowing from the supply air duct to the compartment;a return air duct configured to provide an exit airflow path to the external air system for return air that has circulated throughout the compartment, the return air duct including an outlet port mounted to a surface of the compartment to provide an outlet path for the return air from the compartment to the return air duct; andan airflow adjustment apparatus including an airflow adjustment surface disposed within at least one of the supply airflow path of the supply air duct and the exit airflow path of the return air duct, the airflow adjustment surface configured to cause a modification of airflow properties for air flowing across or through the airflow adjustment surface.2. The ducting assembly of claim 1 , wherein the airflow properties include at ...

Fuselage and aircraft including an air distribution multifunctional substructure and assembly method

An aircraft fuselage including a fuselage skin, cross-members supporting a floor of the aircraft, wherein the fuselage includes a multifunctional substructure fixed to at least one of the cross-members in a lowered part of the cross-member. The multifunctional substructure comprises: at least one duct of an air distribution system having a substantially rectangular section at the location of the at least one cross-member and having lateral walls of the duct that are substantially vertical; a seat fixing track or a stiffener fixed on a first lateral wall of the duct of the multifunctional substructure, and; a seat fixing track or a stiffener fixed on a second lateral wall, opposite the first lateral wall, of the duct of the multifunctional substructure.

CABIN AIR COMPRESSOR MOTOR COOLING FLOW ENHANCEMENT COWL

A cabin air compressor (CAC) motor cooling flow enhancement cowl includes a cowl body contoured to extend from a CAC motor cooling duct discharge of a ram air outlet header. The cowl body includes a backward facing step to form an air dam in a ram air flow path to divert ram system air away from the CAC motor cooling duct discharge. The CAC motor cooling flow enhancement cowl also includes a coupling interface formed at an upstream end of the cowl body to engage with a transition edge of the CAC motor cooling duct discharge. 1. A cabin air compressor (CAC) motor cooling flow enhancement cowl , comprising:a cowl body contoured to extend from a CAC motor cooling duct discharge of a ram air outlet header, the cowl body comprising a backward facing step to form an air dam in a ram air flow path to divert ram system air away from the CAC motor cooling duct discharge; anda coupling interface formed at an upstream end of the cowl body to engage with a transition edge of the CAC motor cooling duct discharge.2. The CAC motor cooling flow enhancement cowl of claim 1 , wherein the cowl body forms a CAC motor cooling duct extension channel with respect to a bell mouth of the ram air outlet header upstream from a ram air fan inlet interface of the ram air outlet header.3. The CAC motor cooling flow enhancement cowl of claim 2 , wherein the CAC motor cooling duct extension channel is sized to partially extend into the bell mouth when the coupling interface is engaged with the transition edge of the CAC motor cooling duct discharge.4. The CAC motor cooling flow enhancement cowl of claim 2 , wherein the CAC motor cooling duct extension channel is sized to extend in the bell mouth beyond the ram air fan inlet interface when the coupling interface is engaged with the transition edge of the CAC motor cooling duct discharge.5. The CAC motor cooling flow enhancement cowl of claim 2 , wherein a channel height of the CAC motor cooling duct extension channel is less than a channel height ...

Apparatus and Method for Locational Aiming of an Overhead Directional Service Unit

An apparatus for locational aiming of an overhead directional service unit includes a body including a first end configured to be matingly engaged with a housing assembly of the overhead directional service unit and a second end longitudinally opposed to the first end. A light source is disposed within the body and operable to project a light beam from the second end in a direction defined by a longitudinal axis of the body. With the first end matingly engaged with the housing assembly, pivotal movement of the body about a pivot axis relative to a mounting assembly of the overhead directional service unit applies a leverage force to the housing assembly to pivotally reposition the housing assembly relative to the mounting assembly so that the housing assembly is directionally aimed toward a target location visually indicated by the light beam.

METHODS AND DEVICE FOR MIXING AIRFLOWS IN ENVIRONMENTAL CONTROL SYSTEMS

Methods and a device for mixing airflows in an environmental control system are provided. The device includes a duct configured to receive a first airflow and a second airflow, and a plurality of guide vanes disposed within said duct. The guide vanes are configured to induce rotation of the first and second airflows flowing through the duct. 1. A device for use in mixing airflows in an environmental control system , said device comprising:a duct configured to receive a first airflow and a second airflow; anda plurality of guide vanes disposed within said duct and configured to induce rotation of the first and second airflows flowing through said duct.2. A device in accordance with claim 1 , wherein said plurality of guide vanes is positioned between an injection site of the second airflow into the first airflow and a temperature sensor configured to measure a temperature of the mixed first and second airflows.3. A device in accordance with claim 2 , wherein said plurality of guide vanes is positioned to mix the first and second airflows before a temperature of the mixed first and second airflows is measured.4. A device in accordance with claim 2 , wherein the temperature sensor is positioned to measure a temperature at a point where the first and second airflows are substantially mixed.5. A device in accordance with claim 2 , wherein a temperature measurement is used to control an amount of the second airflow injected into the first airflow.6. A device in accordance with claim 1 , wherein said plurality of guide vanes are configured to force axial flows of the first airflow and the second airflow into a rotational movement to generate a swirl flow as the first and second airflows flow through said duct.7. A device in accordance with claim 1 , wherein said plurality of guide vanes project from an inner surface of said duct and are circumferentially spaced at equal intervals.8. A device in accordance with claim 1 , wherein said plurality of guide vanes are curved ...

FILTER AND METHOD FOR PRODUCING SAME

A filter for binding constituents of a gas stream includes a supporting member and a filter layer applied to surfaces of the supporting member. The filter layer includes a component for the physisorption of constituents, a component for the chemisorption of constituents, and a component for dissolving oil constituents which comprises ionic liquids. 1. A filter for binding constituents of a gas stream , the filter comprising:a supporting member; anda filter layer applied to the surfaces of the supporting member, a) a component for the physisorption of constituents,', 'b) a component for the chemisorption of constituents, and', 'c) a component for dissolving oil constituents which comprises ionic liquids., 'wherein the filter layer includes2. The filter as claimed in claim 1 , wherein the supporting member is at least one of a ceramic supporting member or a metal supporting member.3. The filter as claimed in claim 1 , wherein the supporting member has a cell density of from 50 to 1600 cpsi.4. The filter as claimed in claim 1 , wherein claim 1 , under application conditions claim 1 , the filter has a pressure drop of 10 mbar or less.5. The filter as claimed in claim 1 , wherein the component for the physisorption includes at least one of activated carbon claim 1 , bentonite claim 1 , siliceous earths claim 1 , or zeolites.6. The filter as claimed in claim 1 , wherein the component for the chemisorption comprises at least one of peptides or proteins.7. The filter as claimed in claim 1 , wherein the component for the chemisorption comprises keratin-containing fibers.8. The filter as claimed in claim 1 , wherein the ionic liquids comprise cations selected from the group consisting of: optionally alkylated imidazolium claim 1 , pyridinium claim 1 , pyrrolidinium claim 1 , guanidinium claim 1 , uronium claim 1 , thiouronium claim 1 , piperidinium claim 1 , morpholinium claim 1 , ammonium and phosphonium ions and anions selected from the group consisting of ...

LOW PRESSURE ENVIRONMENTAL CONTROL SYSTEM WITH SAFE PYLON TRANSIT

A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. A pylon supports the engine. The pylon defines a lowermost surface and the higher pressure tap extends above a plane including the lowermost surface. The higher pressure tap includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon. An environmental control system is also disclosed. 1. A gas turbine engine comprising:a fan section delivering air into a compressor section, said compressor section compressing air and delivering air into a combustion section, products of combustion passing from said combustion section over a turbine section to drive said fan section and main compressor sections, wherein a gearbox is driven by said turbine section to drive said fan sectionan environmental control system including a higher pressure tap at a higher pressure location in ...

APPARATUS AND METHOD FOR AIRFLOW MODIFICATION IN VEHICLES

Provided is an air-diverter apparatus configured to modify the directional airflow in an aircraft cabin. A nozzle may be provided that includes a body having a longitudinal axis, an inlet configured to be connected to a source of air, a flow passage in communication with the inlet and extending through the body, and an outlet in communication with the flow passage, wherein the outlet is angled relative to the longitudinal axis. 1. A nozzle configured to be positioned in a plate , the nozzle including:a body having a longitudinal axis, an inlet configured to be connected to a source of air, a flow passage in communication with the inlet and extending through the body, and an outlet in communication with the flow passage,wherein the outlet is angled relative to the longitudinal axis.2. The nozzle according to claim 1 , wherein the flow passage is angled relative to the longitudinal axis to direct airflow toward the outlet.3. The nozzle according to claim 1 , further comprising a flow straightener disposed in the flow path claim 1 , the flow straightener configured to control a path of airflow through the flow passage.4. The nozzle according to claim 3 , wherein the body includes ledges in the flow passage for engaging with the flow straightener to hold the flow straightener in the body.5. The nozzle according to claim 1 , wherein the body includes a cylindrical portion and a head portion extending from the cylindrical portion claim 1 , wherein an end of the cylindrical portion defines the inlet and wherein the outlet is located in the head portion.6. The nozzle according to claim 5 , further comprising one or more arms projecting upward from the cylindrical portion claim 5 , each of the one or more arms having at least one tab for engaging a slot in the plate.7. The nozzle according to claim 5 , further comprising threads on an outer surface of the cylindrical portion for engaging corresponding threads on the plate.8. A nozzle assembly including a plurality of nozzles ...

AIRCRAFT SEATS WITH AIR VENTS

An aircraft passenger seat ventilation system is disclosed. The ventilation system comprises one or more passenger seats, one or more partitions at a respective armrest portion of the one or more passenger seats, one or more vents along one or more sides of the one or more partitions comprising a plurality of holes, and a suction source configured to suction air from the one or more vents to an air filtration system. The ventilation system provides hygienic travel experiences for passengers and crew members by minimizing the spread of viruses and/or bacteria within the aircraft cabin caused by turbulent air flow. 1. An aircraft passenger seat ventilation system , comprising:one or more passenger seats;one or more partitions, wherein each of the one or more partitions is at a respective armrest portion of the one or more passenger seats;one or more vents along one or more sides of the one or more partitions, wherein each of the one or more vents comprises a plurality of holes; anda suction source configured to suction air from the one or more vents to an air filtration system.2. The aircraft passenger seat ventilation system of claim 1 , wherein each of the one or more partitions comprises an upper partition above the armrest portion and a lower partition below the armrest portion.3. The aircraft passenger seat ventilation system of claim 2 , wherein the one or more vents comprise upper vents along the upper partition and lower vents along the lower partition.4. The aircraft passenger seat ventilation system of claim 3 , wherein the upper vents are configured to suction air substantially adjacent to a head or a torso of a user claim 3 , wherein the lower vents are configured to suction air substantially adjacent to the legs of the user.5. The aircraft passenger seat ventilation system of claim 1 , wherein the one or more partitions includes at least one medial partition having a first side and a second side claim 1 , wherein the one or more vents includes first vents ...

RAM AIR CHANNEL ASSEMBLY AND METHOD FOR OPERATING A RAM AIR CHANNEL ASSEMBLY

An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets. 1. A ram air channel assembly for an aircraft , comprising:a first ram air inlet having a protruding portion which protrudes from an outer surface of a section of an aircraft outer skin, wherein the first ram air inlet is coupled to a first ram air inlet channel;a second ram air inlet having a cross-sectional area arranged flush with the section of the aircraft outer skin, wherein the second ram air inlet is coupled to a second ram air inlet channel and arranged proximate to the first ram air inlet at a predetermined distance from the first ram air inlet upstream of the first ram air inlet;a flap which, at least in sections, is pivotable about an axis relative to the section of the aircraft outer skin between a first and a second operating position, wherein the axis is arranged upstream of the first and the second ram air inlet and extends in a direction substantially perpendicular to a direction of flow of an air flow passing the section of the aircraft outer skin; and,a control unit for controlling an operation of the flap, the control unit being adapted to control the flap into its first operating position when the ...

INTEGRATED ENVIRONMENTAL CONTROL SYSTEMS AND METHODS FOR CONTROLLING ENVIRONMENTAL TEMPERATURE OF AN ENCLOSED SPACE

Environmental control systems and methods to control environmental temperature of an enclosed space by integrating a passive heat exchange subsystem (e.g., a loop heat pipe (LHP) heat exchange subsystem) having a closed loop heat exchange fluid circuit in heat-exchange relationship with the enclosed space for providing environmental temperature control therewithin, a RAM-air subsystem having a RAM-air circuit for circulating RAM cooling air, and a vapor compression cycle machine (VCM) subsystem having a VCM fluid circuit having a compressor, an evaporator, a condenser and an expansion valve. 1. An environmental control system for controlling environmental temperature of an enclosed space comprising:a passive phase change heat exchange subsystem having a closed loop heat exchange fluid circuit in heat-exchange relationship with the enclosed space for providing environmental temperature control therewithin;a second RAM-air subsystem having an air circuit for circulation of cooling air; anda third vapor closed loop compression cycle machine (VCM) subsystem having a VCM fluid circuit comprising a compressor, an evaporator, a condenser and an expansion valve, whereinthe evaporator of the VCM subsystem is in operative heat-exchange relationship with the heat exchange fluid circuit of the passive heat exchange subsystem, and whereinthe condenser of the VCM subsystem is in operative heat-exchange relationship with the air circuit of the RAM-air subsystem.2. The environmental control system of claim 1 , wherein the passive heat exchange subsystem comprises a primary condenser in operative heat-exchange relationship with the VCM evaporator of the VCM subsystem.3. The environmental control system of claim 2 , wherein the passive heat exchange subsystem comprises a secondary skin heat exchange (SHX) condenser claim 2 , and a control valve for directing the working fluid to either the primary condenser or the secondary SHX condenser.4. The environmental control system of claim 2 ...

CABIN AIR INLET MODULE AND CABIN AIR SYSTEM

The invention relates to a cabin air inlet module (). The cabin air inlet module () comprises a streaming channel body (). The streaming channel body () comprises at least one wall which limits a streaming channel wherein incoming air () is supplied to a zone () of a cabin (). The cabin air inlet module () comprises an electric heating element () which is used for heating the incoming air (). According to the invention it is proposed that the electric heating element () is embodied as a two-dimensional heating element (in particular as a heating paper, a heating web, a heating foil or a heating varnish). The two-dimensional heating element extends along a wall of the streaming channel body (). 1. A cabin air inlet module comprisinga) a streaming channel body having at least one streaming channel and at least one wall, the wall limiting the streaming channel so that incoming air passing through the streaming channel for being supplied to a cabin is guided by the wall,b) an electric heating element by which it is possible to heat the incoming air,c) the electric heating element being a two-dimensional heating element which extends along the wall.2. The cabin air inlet module of claim 1 , wherein the electric heating elementa) is embedded into the wall orb) contacts the wall and/or is mounted to the wall and established a two-dimensional contact area with the wall.3. The cabin air inlet module of claim 2 , wherein the streaming channel body comprisesa) a streaming tube having a wall andb) at least one guiding element which is arranged in an inner cross section of the streaming tube and which comprises another wall.4. The cabin air inlet module of claim 3 , wherein at least one guiding element which is arranged in the inner cross section of the streaming tube has a shape of a spiral or helix.5. The cabin air inlet module of claim 4 , wherein at a location interior from the guiding element which has the shape of a helix or spiral a free transfer cross section is provided ...

COMPRESSOR TEMPERATURE CONTROL SYSTEM AND METHOD

A compressor temperature control system and method for an aircraft air cycle machine is presented. The system prevents overheating of the compressor using a low limit valve positioned between a turbine outlet and a bleed air source. The low limit valve directs the air to an air cycle machine, or bypasses the machine, in regards at least in part to the air temperature measured in the cabin supply duct. 1. A process for preventing overheating of a compressor in an aircraft air cycle system , the process comprising:receiving bleed air from a bleed air source;compressing the bleed air, thus elevating the air temperature of the bleed air;releasing the air from a compressor outlet;a turbine configured to receive the air from the compressor into a turbine, and expanding the air resulting in a decreasing the air temperature, the expanded air being released from a turbine outlet, and then being introduced into a cabin of the aircraft;positioning a low-limit control valve between the source of bleed air, the turbine outlet, and the cabin;sensing temperature at different locations in the system;a plurality of sensors positioned in different locations in said system;receiving readings from the plurality of sensors and using the readings to determine an extent of openness of the low-limit control valve to enable a portion of the bleed air to bypass the compressor, thus lowering the compressor operating temperature for the purpose of preventing an overheating of the compressor.2. The process of comprising:utilizing whichever of a determined first, second, or third low-limit valve adjustment based on which of the first, second, and third adjustment has the highest value while an air temperature reading from the cabin supply duct is within a normal temperature range.3. The process of claim 2 , comprising:utilizing the first low-limit adjustment when an air temperature reading from the cabin supply duct is in a temperature range indicative of being close to an overheat condition.4. ...

LEADING EDGE MEMBER FOR AN AIRFOIL OF AN AIRCRAFT

A leading edge member, an airfoil and an aircraft using the leading edge member to improve de-icing capacity by recirculating hot bleed air in a spanwise direction and to increase the mass and heat flow within the leading edge member. The hot bleed air is injected via an inlet arrangement into a forward hot air chamber defined by the outer skin of the leading edge member and the front spar. Subsequently, the hot air flow travels through a connecting passage opening from the forward hot air chamber through the front spar into the aft hot air chamber. Subsequently, the hot air flows along the entire spanwise length within the aft hot air chamber and splits into an exhaust flow and a recirculation flow. The recirculation flow passes through a recirculation opening and mixes with new hot bleed air, to take another round trip within the leading edge member. 1. A leading edge member of an airfoil of an aircraft , the leading edge member having an outer skin and a de-icing device , the de-icing device comprising:a forward hot air chamber and an aft hot air chamber, the forward and aft hot air chambers extending along a spanwise direction of the leading edge member and being separated by a separation wall along the spanwise direction, the separation wall being configured so as to allow for a circular hot air flow in the spanwise direction; andan inlet arrangement having at least one inlet opening for injecting hot air, the inlet arrangement configured for generating a circular hot air flow within the de-icing device,wherein the de-icing device is configured such that the circular hot air flow causes a hot air recirculation flow from the aft hot air chamber to the forward hot air chamber.2. The leading edge member according to claim 1 , wherein the de-icing device comprises a recirculation opening which fluidly connects the aft hot air chamber to the forward hot air chamber and which is arranged such that the hot air recirculation flows from the aft hot air chamber through ...

GAS TURBINE ENGINE COMPRESSOR CONTROL METHOD

A method of operating a gas turbine engine compressor. The engine comprises a compressor having an environmental control system bleed port having an outlet in fluid communication with an aircraft environmental control system air duct, and an air turbine starter configured to rotate a compressor shaft of the gas turbine engine. The air turbine starter has an inlet in fluid communication with the environmental control system air duct via an air turbine valve. The method comprises determining a surge margin of the compressor, and where the surge margin of the compressor is determined to be below a predetermined minimum surge margin, opening the air turbine valve to supply air to the air turbine. 1. A method of operating a gas turbine engine compressor , the engine comprising:a compressor having an environmental control system bleed port having an outlet in fluid communication with an aircraft environmental control system air duct;and an air turbine starter configured to rotate a compressor shaft of the gas turbine engine, the air turbine starter having an inlet in fluid communication with the environmental control system air duct via an air turbine valve, wherein the method comprises:determining a surge margin of the compressor; andwhere the surge margin of the compressor is determined to be below a predetermined minimum surge margin, opening the air turbine valve to supply air to the air turbine.2. A method according to claim 1 , wherein the method comprises determining whether an environmental control system air conditioning system which communicates with the environmental control system air duct is functioning claim 1 , and if it is not functioning claim 1 , and the surge margin of the compressor is determined to be below the predetermined minimum surge margin claim 1 , opening the air turbine valve to supply air to the air turbine.3. A method according to claim 1 , wherein the surge margin is one of a current measured surge margin and a predicted future surge ...

Air supply system for an aircraft

An air supply system for a gas turbine engine including a first duct which is connected or capable of being connected to a first compressor bleed air supply of a gas turbine engine; a second duct which downstream of the first compressor bleed air supply is connected or capable of being connected to a second compressor bleed air supply of the gas turbine engine; a nozzle by way of which air from the second duct is capable of being blown into the first duct; and an exhaust air duct having an opening which downstream of the nozzle is disposed in the first duct in such a manner that air blown by way of the nozzle into the first duct can flow out of the first duct through the opening into the exhaust air duct. A gas turbine engine and an aircraft are furthermore provided.

AIRCRAFT TURBOMACHINE COMPRISING A DEFLECTOR

An aircraft turbomachine comprising a fan conduit with a wall, a flow of air passing through the turbomachine via the fan conduit. An air passage comprising an air opening is arranged in the wall, the air passage configured to receive a portion of the flow of the air through the fan conduit. A deflector is fixed to the wall upstream of the air opening, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air. The at least one cross-section is porous. The deflector protects the air passage structure and is easy to produce and to fix to the wall of the fan conduit when it is screwed or riveted directly thereto. The deflector, as a result of its location in the fan conduit, is easy to access and thus allows rapid maintenance operations without having to disassemble the air passage. 1. An aircraft turbomachine comprising:a fan conduit comprising a wall, a flow of air through the aircraft turbomachine passing via the fan conduit;an air passage comprising an air opening arranged in the wall, the air passage being configured to receive a portion of the flow of the air of the fan conduit;a deflector fixed to the wall upstream of the air opening in the flow direction of the air, the deflector comprising at least one cross-section extending in the fan conduit to capture the flow of air,wherein the at least one cross-section is porous.2. The turbomachine as claimed in claim 1 , wherein the cross-section is porous and comprises a plurality of elements for the air passage which are arranged on the cross-section.3. The turbomachine as claimed in claim 2 , wherein the elements for the air passage comprise at least one of through-holes and notches.4. The turbomachine as claimed in claim 3 , wherein the through-holes have a diameter greater than or equal to 2 mm and less than or equal to 4 mm.5. The turbomachine as claimed in claim 3 , wherein the through-holes all have the same diameter.6. The turbomachine as claimed in claim 3 , ...

Solar powered drone

A solar power system for a drone. The system including a shell with at least one solar cell adapted for placement on an exterior surface of a drone. The system coupled to a controller, the controller distributing collected solar energy to the various systems of the drone including the power systems containing batteries and the motor systems adapted to propel the drone.

METHOD OF INSTALLING A DIFFUSER IN AN AIR CYCLE MACHINE

A method of installing a diffuser in an air cycle machine includes placing a first housing on a shaft, placing a seal plate on the shaft, and placing a diffuser on the shaft. Next, the diffuser and the seal plate are aligned with an alignment tool. The alignment tool has a first annular surface to align with a radially outer surface of the seal plate and a second annular surface to align with an annular flange on the diffuser. Finally, the diffuser is fastened to the seal plate and the alignment tool is removed from the diffuser and the seal plate. 1. An alignment tool that can be used to install a diffuser in an air cycle machine , the alignment tool comprising:a body with a cylindrical portion and an end portion;a first surface on a radially inner face of the cylindrical portion positioned axially away from the end portion;a second surface on the radially inner face of the cylindrical portion positioned adjacent to the end portion; anda third surface on a radially inner edge of the end portion.2. The alignment tool of claim 1 , wherein the first surface has a larger diameter than the second surface.3. The alignment tool of claim 1 , wherein the first surface is configured to have a diameter that is substantially equal to a diameter of a radially outer surface of a seal plate in the air cycle machine.4. The alignment tool of claim 1 , wherein the third surface is configured to have a diameter that is substantially equal to a diameter of a radially outer surface of a flange on the diffuser in the air cycle machine.5. The alignment tool of claim 1 , wherein the first surface and the third surface are precision manufactured.6. The alignment tool of claim 1 , and further comprising:a plurality of openings in the cylindrical portion of the alignment tool.7. The alignment tool of claim 1 , and further comprising:an aperture in the end portion of the alignment tool that is configured to receive a timing pin.8. An alignment tool that can be used to install a diffuser in an ...

AIRCRAFT CABIN DISINFECTION

The disclosure describes a method for disinfecting an aircraft cabin that includes injecting a non-peroxide disinfectant into an environmental control system of an aircraft and discharging cabin supply air through the environmental control system to discharge the non-peroxide disinfectant into the aircraft cabin. In some instances, the method includes aerosolizing the disinfectant into a plurality of liquid droplets while injecting the disinfectant into the environmental control system. In some instances, the injected disinfectant includes a non-corrosive, non-toxic disinfectant, such that the disinfectant may be discharged into the aircraft cabin in the presence of personnel in the aircraft cabin. 1. A method of disinfecting an aircraft cabin , comprising:injecting a non-peroxide disinfectant into an environmental control system of an aircraft; anddischarging supply air through the environmental control system to discharge the non-peroxide disinfectant into the aircraft cabin.2. The method of claim 1 , further comprising aerosolizing the disinfectant into a plurality of liquid droplets while injecting the disinfectant into the environmental control system.3. The method of claim 2 , wherein the plurality of liquid droplets has an average diameter between about 100 nanometers and about 100 micrometers.4. The method of claim 2 , wherein at least 50% of the aerosolized disinfectant vaporizes prior to entering the cabin.5. The method of claim 1 , further comprising vaporizing the disinfectant prior to injecting the disinfectant into the environmental control system.6. The method of claim 1 ,wherein the disinfectant comprises a non-corrosive, non-toxic disinfectant, andwherein the disinfectant is discharged into the aircraft cabin in a presence of personnel in the aircraft cabin.7. The method of claim 1 , further comprising discharging the disinfectant from the aircraft cabin using at least one of an outflow valve or a recirculation fan.8. The method of claim 1 , wherein ...

Air conditioning system for an aircraft cabin, comprising means for reheating the water collected by the water extraction loop

Air conditioning system for a cabin ( 10 ) of an aircraft, comprising: an air bleed device; an air cycle turbine engine ( 12 ); at least one main cooling exchanger ( 16 ); a water extraction loop ( 30 ); and a pipe ( 26 ) for distributing water extracted by said extraction loop ( 30 ), characterized in that said system further comprises means ( 40 ) for heating the water extracted by the water extraction loop so as to be able to spray the water into a ram-air channel ( 22 ) which supplies said main exchanger ( 16 ).

EXCHANGER FOR COOLING WARM PRIMARY AIR WITH COOL SECONDARY AIR AND SYSTEM FOR AIR CONDITIONING PROVIDED WITH SUCH AN EXCHANGER

Exchanger () for cooling hot primary air by means of cold secondary air, comprising: a plurality of channels () for the circulation of the secondary air; and a plurality of channels for the circulation of the primary air, characterized in that said exchanger further comprises: water circulation channels () each extending adjacently to a secondary channel (); water-spray micro-perforated hollow bars () each extending adjacently to a primary channel () and fluidically connected to the micro-perforated hollow bars in order to be able to heat the water by interaction with the primary air before said water is sprayed into the flow of primary air at the inlet of the exchanger. 1. An exchanger for cooling hot primary air by means of cold secondary air , comprising:a plurality of channels, referred to as secondary channels, placed one on top of the other and intended for the circulation of said secondary air, each extending in the same direction, comprising a secondary direction, between an air inlet, comprising a secondary air inlet, and an air outlet, comprising secondary air outlet; anda plurality of channels, comprising primary channels, for the circulation of said primary air, each interposed between two secondary channels and extending in the same direction, comprising a primary direction, which is different from said secondary direction, between an air inlet, referred to as the primary air inlet, and an air outlet, comprising a primary air outlet so as to allow heat exchanges between the primary air of said primary channels and the secondary air of said secondary channels;wherein said exchanger further comprises:water circulation channels, each extending adjacently to a secondary channel in said secondary direction in the vicinity of the primary air outlets, between a water inlet and a water outlet, so as to allow this water to be heated by heat exchanges with said flow of primary air of said primary channels; andwater-spray micro-perforated hollow bars, each ...

VANE ASSEMBLY FOR DISTRIBUTION OF A STRATIFIED FLUID IN AN AIRCRAFT

A vane assembly for distribution of a stratified fluid in an aircraft is taught herein. The vane assembly includes a housing including a housing inlet and a housing outlet. The housing inlet is configured to receive the stratified fluid with the stratified fluid including a first portion and a second portion. The housing outlet is configured to exhaust the stratified fluid. The housing defines an interior housing volume between the housing inlet and the housing outlet. The vane assembly further includes a vane disposed within the interior housing volume and bisecting the interior housing volume. The vane includes a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet. The trailing edge is angularly offset from the leading edge. 1. A vane assembly for distribution of a stratified fluid in an aircraft , the stratified fluid comprising a first portion and a second portion , the vane assembly comprising:a housing comprising a housing inlet and a housing outlet, the housing inlet configured to receive the stratified fluid, the housing outlet spaced from the housing inlet and configured to exhaust the stratified fluid, and the housing defining an interior housing volume between the housing inlet and the housing outlet; anda vane disposed within the interior housing volume and bisecting the interior housing volume, the vane comprising a leading edge adjacent the housing inlet and a trailing edge adjacent the housing outlet, the vane having a first side and a second side opposite the first side, the first side and the second side extending between the leading edge and the trailing edge, and the trailing edge angularly offset from the leading edge relative to the first side and the second side;wherein the first side is configured to direct the first portion between the housing inlet and the housing outlet and the second side is configured to direct the second portion between the housing inlet and the housing outlet.2. The vane assembly of ...

MIXER ASSEMBLY WITH SURROUNDING FILTER ELEMENT, STOWAGE SPACE WITH MIXER ASSEMBLY, VEHICLE WITH A STOWAGE SPACE AND METHOD FOR INSTALLING A MIXER ASSEMBLY

A mixer assembly for mixing two air streams in a ventilation system. The mixer assembly comprises a mixing chamber, which comprises an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber, and also a shroud, which surrounds the mixing chamber wall, at least in certain portions. The shroud forms and delimits an intermediate space between the mixing chamber wall and the shroud. The mixer assembly also comprises a filter element, which fluidically connects the intermediate space to a surrounding area of the mixer assembly, the intermediate space being fluidically connected to the mixing chamber. Fluid can thus flow through the filter element into the intermediate space and further into the mixing chamber. A stowage space with a mixer assembly, an aircraft with such a stowage space and a method for producing a mixer assembly in an aircraft are also described. 1. A mixer assembly for mixing two air streams in a ventilation system , the mixer assembly comprising:a mixing chamber comprising an inlet and an outlet and a mixing chamber wall delimiting the mixing chamber;a shroud surrounding the mixing chamber wall, at least in certain portions, the shroud delimiting an intermediate space between the mixing chamber wall and the shroud, and the filter element fluidically connecting the intermediate space to a surrounding area of the mixer assembly, and', 'the intermediate space being fluidically connected to the mixing chamber., 'a filter element,'}2. The mixer assembly according to claim 1 , the filter element being arranged detachably on the mixer assembly and abutting the shroud.3. The mixer assembly according to claim 2 , the filter element having on a side facing the shroud a contour which corresponds claim 2 , at least in certain portions claim 2 , to a contour of an outer side of the shroud.4. The mixer assembly according to claim 1 , further comprising:a conveying device configured to convey a fluid through the filter element into the ...

PASSENGER CABIN AIR DISTRIBUTION SYSTEM AND METHOD OF USING

A passenger cabin air distribution system includes a ventilation system and an ejector-diffuser. The ventilation system is operable to provide a conditioned air. The ejector-diffuser is positioned to receive a flow of the conditioned air from the ventilation system. The ejector-diffuser includes an induction unit and a diffuser section. The induction unit includes a secondary inlet in communication with a cabin air from a passenger cabin and is configured to mix the flow of the conditioned air with an induced flow of the cabin air into a mixed air. The diffuser section includes a discharge to eject the mixed air to the passenger cabin. The diffuser section is shaped to provide for efficient mixing with low backpressure in order to maintain the low motive pressure in the nozzle. 1. A passenger cabin air distribution system comprising:a ventilation system operable to provide a conditioned air; andan ejector-diffuser having a nozzle positioned to receive a flow of the conditioned air from the ventilation system, the ejector-diffuser including an induction unit and a diffuser section, the induction unit including a secondary inlet in communication with a cabin air from a passenger cabin and configured to mix the flow of the conditioned air with an induced flow of the cabin air into a mixed air, the diffuser section including a discharge to eject the mixed air to the passenger cabin, the flow of the conditioned air within the nozzle having a low motive pressure.2. The passenger cabin air distribution system of claim 1 , wherein an absolute pressure ratio of the conditioned air within the nozzle to the cabin air in the passenger cabin is approximately 1.002.3. The passenger cabin air distribution system of claim 1 , wherein the ejector-diffuser further comprises:a first end having a primary inlet coupled to the ventilation system to receive the conditioned air;a second end opposite the first end, the discharge at the second end;the nozzle positioned between the first end ...

Restricted Space Air Chiller

An aircraft galley chiller is adapted to fit within a service column of the aircraft. The condenser is elongated, oriented vertically, and includes a bank of fans to increase airflow. The evaporator is also elongated and includes a bank of fans. The evaporator and condenser are oriented with the same plane to produce a footprint that fits within the service column. The evaporator includes a heater element to periodically heat and de-ice the evaporator. 1. A chiller comprising:a condenser;a bank of condenser fans corresponding to the condenser configured to circulate air through the condenser;an air-cooling element in fluid communication with the condenser a bank of evaporator fans configured to circulate air through the air-cooling element, the condenser and bank of condenser fans are linearly elongated and disposed along a first edge of the chiller;', 'the bank of evaporator fans is disposed linearly along a second edge of the chiller; and', 'the disposition of the condenser and bank of condenser fans, and evaporator fans define a chiller envelope configured to fit within a service column of an aircraft., 'wherein2. The chiller of claim 1 , wherein the cooling element comprises an evaporator claim 1 , and further comprising a heating element corresponding to the evaporator.3. The chiller of claim 2 , further comprising a processor configured to:identify one or more parameters for a defrost cycle;activate the heating element; andreverse the direction of the bank of evaporator fans.4. The chiller of claim 3 , further comprising a louvered inlet disposed on the evaporator claim 3 , wherein the louvered inlet comprises a plurality of fins configured to close via air pressure from the bank of evaporator fans operating in reverse.5. The chiller of claim 3 , further comprising a louvered inlet disposed on the evaporator claim 3 , wherein the louvered inlet comprises:a plurality of fins; andat least one motor configured to close the plurality of fins when the bank of ...

FAN ROTOR PILOTING

A fan rotor has a plurality of blades arranged circumferentially about a central axis, wherein the plurality of blades extend between 2.9980 and 3.0020 inches radially from the central axis. The fan rotor has a root portion arranged radially inward from the plurality of blades. The fan rotor also has a web portion that connects the plurality of blades to the root portion, the web portion having a minimum longitudinal thickness between 0.2000 and 0.2100 inches. 1. A fan rotor comprising:a plurality of blades arranged circumferentially about a central axis, wherein the plurality of blades extend between 7.6149 and 7.6251 centimeters radially from the central axis;a root portion arranged radially inward from the plurality of blades; anda web portion that connects the plurality of blades to the root portion, the web portion having a minimum longitudinal thickness between 0.5080 and 0.5334 centimeters.2. The fan rotor of claim 1 , wherein the root portion defines an inner surface circumscribing the central axis claim 1 , the inner surface having a diameter between 0.6896 and 0.6922 centimeters.3. The fan rotor of claim 2 , wherein the diameter of the inner surface is between 0.6904 and 0.6914 centimeters.4. The fan rotor of claim 1 , wherein the root portion comprises a first foot extending in a first longitudinal direction from the web portion claim 1 , the first foot comprising an annular structure having an outer diameter between 1.379 and 1.380 centimeters.5. The fan rotor of claim 4 , wherein the outer diameter of the first foot is between 1.3795 cm and 1.3800 cm.6. The fan rotor of claim 4 , wherein the root portion comprises a second foot portion extending in a second longitudinal direction from the web portion claim 4 , wherein:the second longitudinal direction is opposite the first longitudinal direction; andthe second foot portion comprises an annular structure having an outer diameter between 1.4173 and 1.4183 centimeters.7. The fan rotor of claim 6 , wherein ...

AUXILLARY POWER UNIT ASSEMBLY AND A METHOD OF USING THE SAME

A gas turbine auxiliary power unit system for an aircraft comprises an aircraft cabin provided with a pressurised air supply, a gas turbine engine comprising a compressor assembly, and a controller. 1. A gas turbine auxiliary power unit system for an aircraft , the system comprising:an aircraft cabin provided with a pressurised air supply;a gas turbine engine comprising a compressor assembly; anda controller,wherein the pressurised air supply is provided to the aircraft cabin through an aircraft cabin air inlet, and exhausted from the aircraft cabin through an aircraft cabin air exhaust,the gas turbine engine is provided with an inlet air flow from the aircraft cabin air exhaust, andthe controller is operable to control a flow rate of a fuel supplied to the gas turbine engine responsive to a power demand on the auxiliary power unit, the controller being further operable to restrict an inlet air flow into the gas turbine engine, so as to maintain an air pressure inside the aircraft cabin within a pre-determined range.2. The system as claimed in claim 1 , wherein the gas turbine engine comprises a plurality of actuatable variable inlet guide vanes claim 1 , each of the variable inlet guide vanes being controlled by the controller to restrict the inlet air flow into the gas turbine engine.3. The system as claimed in claim 2 , wherein the compressor assembly comprises the plurality of variable inlet guide vanes.4. The system as claimed in claim 1 , wherein the gas turbine engine further comprises:a coupled power turbine assembly, the coupled power turbine assembly being connected to the compressor assembly by a first shaft; anda throttle assembly in fluid communication with the compressor assembly;wherein the controller is operable to control the throttle assembly to restrict the inlet air flow into the gas turbine engine.5. The system as claimed in claim 4 , the system further comprising a first electrical generator claim 4 , the first electrical generator being ...

AIRCRAFT INSULATION SYSTEM AND AIRCRAFT AIR CONDITIONING AND INSULATION ARRANGEMENT

An aircraft insulation system comprising a foil extending at a distance from an inner surface of an aircraft outer shell. An air gap is defined between the foil and the aircraft outer shell. A cabin exhaust air duct is arranged adjacent to an inner surface of the foil and being adapted to have cabin exhaust air flow through the duct. 1. An aircraft insulation system comprising:a foil extending at a distance from an inner surface of an aircraft outer shell,an air gap defined between the foil and the aircraft outer shell, anda cabin exhaust air duct arranged adjacent to an inner surface of the foil and being adapted to allow cabin exhaust air to flow through the duct.2. The aircraft insulation system according to claim 1 , wherein the cabin exhaust air duct comprises a cabin exhaust air outlet arranged in a ceiling region of an aircraft cabin.3. The aircraft insulation system according to claim 1 , wherein the cabin exhaust air duct extends from the ceiling region of the aircraft cabin substantially parallel to the aircraft outer shell into a lower deck of the aircraft.4. The aircraft insulation system according to claim 1 , further comprising a control unit adapted to control a flow of cabin exhaust air through the cabin exhaust air duct in such a manner that the cabin exhaust air claim 1 , upon flowing through the cabin exhaust air duct claim 1 , is cooled to a temperature of approximately 5° C. to 10° C.5. The aircraft insulation system according to claim 1 , wherein the foil is made of a watertight material.6. The aircraft insulation system according to claim 1 , wherein the foil is made of an airtight material.7. The aircraft insulation system according to claim 1 , wherein the foil comprises a plurality of foil sheets attached to an aircraft primary structure claim 1 , the foil sheets extending between pairs of adjacent frames of the aircraft primary structure.8. The aircraft insulation system according to claim 7 , wherein the foil sheets are attached to the ...

AIRCRAFT HAVING A REDUNDANT AND EFFICIENT BLEED SYSTEM

An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin includes an environmental control system having at least one pneumatic air cycle air conditioning unit, a bleed air port in the at least one thrust providing jet engine, a non thrust providing auxiliary supply unit configured to provide electricity and compressed air on ground and during flight, and at least one compressed air line. The at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit. The environmental control system is coupled with the at least one compressed air line. Further, the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air, and bleed air from the bleed air port is selectively providable to the environmental control system for redundancy. 1. An aircraft having at least one thrust providing jet engine and a fuselage with an integrated pressurized cabin , the aircraft comprising:an environmental control system comprising at least one pneumatic air cycle air conditioning unit;a bleed air port in the at least one thrust providing jet engine;a non thrust providing auxiliary supply unit adapted for providing electricity and compressed air on ground and during flight; andat least one compressed air line;wherein the at least one compressed air line is coupled with the bleed air port and the auxiliary supply unit;wherein the environmental control system is coupled with the at least one compressed air line;wherein the auxiliary supply unit is dimensioned to exclusively operate the environmental control system by delivering compressed air; andwherein bleed air from the bleed air port is selectively providable to the environmental control system for redundancy.2. The aircraft according to claim 1 , wherein the auxiliary supply unit comprises at least one fuel cell claim 1 , a compressor and an electric motor coupled with the compressor and ...

PEROXIDE-GENERATING AIR PURIFICATION ELEMENT

A system includes an airflow passage and an air purification element. The airflow passage is configured to confine a flow of air and direct the flow of air toward a space. The air purification element is positioned in the airflow passage and configured to produce a peroxide to oxidize contaminants in air flowing through the airflow passage. The air purification element includes a peroxide-generating structure and a matrix containing a peroxide-activating catalyst configured to activate peroxide produced. The air purification element is configured to produce the peroxide from a water vapor and oxygen in the air within the airflow passage when energized by an energy source, and the matrix is configured to allow the contaminants to contact peroxide activated by the peroxide-activating catalyst. 1. A system , comprising:an airflow passage configured to confine a flow of air and direct the flow of air toward a space; and a peroxide-generating structure configured to produce the peroxide from a water vapor and oxygen in the air within the airflow passage when energized by an energy source; and', 'a matrix containing a peroxide-activating catalyst configured to activate peroxide produced, the matrix being configured to allow the contaminants to contact peroxide activated by the peroxide-activating catalyst., 'an air purification element positioned in the airflow passage and configured to produce a peroxide to oxidize contaminants in air flowing through the airflow passage, the air purification element including2. The system of claim 1 , wherein the peroxide-generating structure comprises an electrode pair separated by an ionically conductive matrix claim 1 , and an electrocatalyst.3. The system of claim 1 , wherein the peroxide-generating structure comprises titanium dioxide.4. The system of claim 1 , wherein the system comprises an aircraft claim 1 , and the airflow passage in which the air purification element is positioned is configured to provide air to a cabin of the ...

INFECTION PREVENTING DEVICE

An infection preventing device includes air barrier forming units that include an air inlet for taking in air from a rear in a front-rear direction, an air purification mechanism for creating clean air by purifying the air taken in from the air inlet, and an air outlet for blowing the clean air toward the front in the front-rear direction, and are capable of blowing out the clean air from the air outlet in the form of layer perpendicular to the left-right direction. The air barrier forming units provided on the seats adjacent in the front-rear direction face in the front-rear direction, and it is configured that air including clean air blown out of the air outlet of the rear air barrier forming unit can be taken in by the air inlet of the front air barrier forming unit. 1. An infection preventing device that is mounted , for suppressing infection among a plurality of passengers , on a vehicle comprising a plurality of seats for the plurality of passengers , the plurality of seats being aligned in a front-rear direction and a left-right direction as viewed when seated in the seats , the infection preventing device comprising:air barrier forming units that comprise an air inlet for taking in air from the rear in the front-rear direction, an air purification mechanism for creating clean air by purifying the air taken in from the air inlet, and an air outlet for blowing the clean air toward the front in the front-rear direction, and are capable of blowing out the clean air from the air outlet in the form of layer perpendicular to the left-right direction,wherein the air barrier forming unit is provided at each of side ends of seat backs of the plurality of seats, the air barrier forming units provided on the seats adjacent in the front-rear direction face in the front-rear direction, and it is configured that air including clean air blown out of the air outlet of the rear air barrier forming unit can be taken in by the air inlet of the front air barrier forming unit.2. ...

CABIN OUTFLOW AIR ENERGY OPTIMIZED CABIN PRESSURIZING SYSTEM

A pressurization system includes a first compressor that receives a ram air, a fan air, or engine air; a first turbine that is on a common shaft with the first compressor and wherein the first turbine receives an engine air; a main heat exchanger downstream of the first compressor and the first turbine; an internal environment suitable for human occupants and downstream of the main heat exchanger; a second turbine downstream of the internal environment; the second turbine may be on the common shaft with the first compressor and first turbine; or a generator downstream of the second turbine; a motor downstream of the generator; and wherein the motor drives the first compressor. 1. A pressurization system that provides a pressurized air to an internal environment suitable for occupants , comprising:a first compressor that receives a ram air, a fan air, or a bleed air;a first turbine that is on a common shaft with the first compressor and wherein the first turbine receives the bleed air;a main heat exchanger downstream of the first compressor and the first turbine, and upstream of the internal environment;a second turbine downstream of the internal environment.2. The system of claim 1 , further comprising a fan air valve upstream of the first compressor.3. The system of claim 1 , further comprising an idling valve upstream of the first compressor.4. The system of claim 1 , further comprising a bleed air valve upstream of the first turbine.5. The system of claim 1 , wherein the second turbine is on the common shaft.6. A pressurization system that provides a pressurized air to an internal environment suitable for occupants claim 1 , comprising:a first compressor that can receive an outside air;a first turbine that is on a first common shaft with the first compressor;a main heat exchanger downstream of the first compressor and the first turbine, and upstream of the internal environment;a generator on a second common shaft with the second turbine; anda motor in ...