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Применить Всего найдено 1914. Отображено 199.
20-08-2011 дата публикации

СПОСОБ РЕГУЛИРОВАНИЯ ДАВЛЕНИЯ ПРОИЗВОДСТВЕННОГО ОТБОРА ПАРА ТЕПЛОФИКАЦИОННОЙ ТУРБИНЫ

Номер: RU2426891C2

Изобретение относится к теплоэнергетике и может быть использовано на электростанциях при эксплуатации теплофикационных турбин. Технический результат изобретения - обеспечение заданного давления пара к потребителю во всем диапазоне изменения величины расхода производственного отбора пара теплофикационной турбины. Указанная задача достигается тем, что в теплофикационной турбине, содержащей органы парораспределения производственного отбора пара и трубопроводы отвода пара к потребителю с установленной на них запорной арматурой, которые используются для обеспечения заданного давления при больших расходах отбора пара, на одном из трубопроводов устанавливают регулирующий клапан, измеряют давление пара за ним, сравнивают его с заданной величиной к потребителю и, при превышении этого давления заданной величины, открывают полностью органы парораспределения производственного отбора, затем перекрывают отвод пара через остальные трубопроводы, обеспечивающие большие расходы, и регулирование давления ...

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10-01-2014 дата публикации

СИСТЕМА УПРАВЛЕНИЯ ОБОРУДОВАНИЕМ С ИЗМЕНЯЕМОЙ ГЕОМЕТРИЕЙ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, СОДЕРЖАЩАЯ, В ЧАСТНОСТИ, БАРАБАННОЕ СОЕДИНЕНИЕ

Номер: RU2503824C2
Принадлежит: СНЕКМА (FR)

Настоящее изобретение касается системы управления, по меньшей мере, двумя типами оборудования с изменяемой геометрией газотурбинного двигателя, содержащего первый корпус и второй корпус, при этом первым оборудованием является ступень статорных лопаток с изменяемым углом установки компрессора первого корпуса, а вторым оборудованием является, по меньшей мере, разгрузочная задвижка компрессора второго корпуса. Система содержит привод, который приводит в движение оба типа оборудования. Привод управляет штоком, на котором установлен барабанный орган управления. Соединение барабанного органа со штоком содержит стержень, размещенный подвижно в направляющей дорожке, а профиль направляющей дорожки определяет закон приведения в движение упомянутого оборудования в зависимости от перемещения штока привода. Такое выполнение системы позволит ее упростить и оптимизировать ее работу. 2 н. и 7 з.п. ф-лы, 7 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 503 824 (13) C2 (51) МПК F01D 17/20 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011117234/06, 29.09.2009 (24) Дата начала отсчета срока действия патента: 29.09.2009 (72) Автор(ы): КОЛОТТ Батист Бенуа (FR), ГОЛЛИ Брюно Робер (FR) (73) Патентообладатель(и): СНЕКМА (FR) R U Приоритет(ы): (30) Конвенционный приоритет: 30.09.2008 FR 0856570 (43) Дата публикации заявки: 10.11.2012 Бюл. № 31 2 5 0 3 8 2 4 (45) Опубликовано: 10.01.2014 Бюл. № 1 2 5 0 3 8 2 4 R U (85) Дата начала рассмотрения заявки PCT на национальной фазе: 03.05.2011 C 2 C 2 (56) Список документов, цитированных в отчете о поиске: DE 1224563 В, 08.09.1966. FR 2445439 А, 25.07.1980. ЕР 1724471 А, 22.11.2006. ЕР 1398464 А, 17.03.2004. WO 2007/116319 А, 18.10.2007. FR 2633046 А, 22.12.1989. RU 2006112001 А, 20.10.2007. RU 2222707 С2, 27.01.2004. RU 2158836 С1, 10.11.2000. (86) Заявка PCT: EP 2009/062624 (29.09.2009) (87) Публикация заявки РСТ: WO 2010/037750 (08.04.2010) Адрес для переписки: 129090, Москва, ул.Б. ...

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20-01-2003 дата публикации

СИСТЕМА УПРАВЛЕНИЯ ОТБОРАМИ ТЕПЛОФИКАЦИОННОЙ ПАРОВОЙ ТУРБИНЫ

Номер: RU2196897C2
Автор: Швец В.М.

Система предназначена для турбин, имеющих как теплофикационные, так и производственные отборы. Система содержит сервомотор части высокого давления и сервомотор части низкого давления с концевыми выключателями, соединенный с регуляторами скорости и отборов пара, снабженными задающими устройствами, сервомотор стопорного клапана, соединенный с золотниками автомата безопасности, и предохранительное устройство регулирования в отборах, выполненное в виде реле давления в отборах, один из которых имеет уставку срабатывания по первому пределу, другие - по более высокому второму пределу, при этом реле давления по второму пределу соединены с золотниками автомата безопасности, логический блок содержит элемент ИЛИ с прямыми и инверсными выходами, реле-повторители и два элемента И, первый из которых имеет инверсный выход, к входам элемента ИЛИ подключены реле давления по первому пределу, прямые выходы элемента ИЛИ подсоединены к входам элементов И, а инверсный выход - к первому управляющему входу переключателя ...

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27-06-2010 дата публикации

СПОСОБ АКТИВНОГО РЕГУЛИРОВАНИЯ ОСЕВОГО ДАВЛЕНИЯ В ПАРОВОЙ ТУРБИНЕ

Номер: RU2393357C2

Изобретения относятся к способу активного регулирования осевого давления в паровой турбине. Способ может включать в себя этапы: осуществления мониторинга осевого давления, воздействующего на узел осевого усилия в паровой турбине; и регулирования осевого давления для поддержания заданного осевого давления на узел осевого усилия в паровой турбине. Такой способ позволяет предотвратить тепловой отказ паровой турбины, повысить ее надежность, долговечность и периоды обслуживания. 8 з.п. ф-лы, 4 ил., 1 табл.

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20-05-2003 дата публикации

СПОСОБ РЕГУЛИРОВАНИЯ ТЕМПЕРАТУРЫ СЕТЕВОЙ ВОДЫ ТЕПЛОФИКАЦИОННОЙ ТУРБОУСТАНОВКИ

Номер: RU2204724C2

Изобретение относится к теплоэнергетике и может быть использовано при эксплуатации теплофикационной турбоустановки. Сущность изобретения заключается в том, что при регулировании температуры сетевой воды теплофикационной турбоустановки после пикового подогревателя, подсоединенного трубопроводом подвода пара с установленным на нем регулирующим органом к камере турбины, выполняют подвод пара к регулирующему органу от двух и более камер турбины, измеряют давление пара в этих камерах, по замеренным давлениям вычисляют температуру насыщения пара каждой камеры, определяют абсолютную разность температур насыщения пара и заданной температуры подогрева сетевой воды и затем осуществляют подвод пара к регулирующему органу из камеры, где эта разность минимальна, а при полном открытии регулирующего органа догрев сетевой воды осуществляют воздействием на парораспределительные органы части высокого давления турбины. Такой способ позволит повысить экономичность теплофикационной турбоустановки при регулировании ...

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20-03-1999 дата публикации

СИСТЕМА РЕГУЛИРОВАНИЯ ЧАСТОТЫ ВРАЩЕНИЯ ПАРОВОЙ МАШИНЫ

Номер: RU2127814C1

Система предназначена для регулирования частоты вращения паровой машины. Система имеет два контура регулирования: парогидравлический и корректирующий электронный. Гидравлический сигнал частоты вращения формируется от давления масляного насоса, связанного с валом паровой винтовой машины (ПВМ). Этот сигнал поступает на чувствительный элемент в виде мембраны, которая управляет клапаном, регулирующим давление в полости парового сервоцилиндра. Последний воздействует на двухседельный клапан, перекрывающий поступление пара в ПВМ. Электрический сигнал частоты вращения установленного на валу ПВМ поступает в электронный регулятор, который вырабатывает сигнал для электрогидравлического преобразователя. Последний корректирует давление на чувствительном элементе. Такое выполнение системы позволяет уменьшить потери давления пара на регулирующем органе и соответственно повысить мощность ПВМ. 1 з.п. ф-лы, 1 ил.

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10-10-2008 дата публикации

СХЕМА УПРАВЛЕНИЯ СЕРВОМОТОРОМ СИСТЕМЫ РЕГУЛИРОВАНИЯ ПАРОВОЙ ТУРБИНЫ

Номер: RU2335639C1

Область использования: изобретение относится к паровым турбинам, а именно: к системам регулирования и защиты паровой турбины. Сущность изобретения: схема управления сервомотором системы регулирования паровой турбины содержит сервомотор, который представляет собой цилиндр с движущимся в нем поршнем; отсечной золотник, управляющий золотник, электромеханический преобразователь, который механически соединен со штоком плунжера управляющего золотника; датчик положения штока поршня сервомотора, датчик положения штока плунжера управляющего золотника. В корпусе сервомотора по образующей выполнены первые два и вторые два окна на уровне первых с образованием штоковой и поршневой полостей соответственно. Плунжеры золотников делят объемы их корпусов на рабочие полости, соответственно соединенные с напорными и сливными магистралями. Золотники гидравлически связаны со штоковой и поршневой полостями сервомотора. Золотник устанавливает поршень сервомотора в исходное состояние по сигналам с командного пункта ...

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09-06-1995 дата публикации

СПОСОБ УПРАВЛЕНИЯ ПОТОКОМ ПАРА В ПАРОВОЙ ТУРБИНЕ С ПРОТИВОТОЧНЫМИ ЦИЛИНДРАМИ

Номер: RU2037052C1

Использование: в системах регулирования и управления потоком рабочей среды в турбомашинах. Сущность изобретения: управление потоком пара осуществляется путем перепуска части пара в одном из цилиндров между ступенями высокого и пониженного давлений при изменении расхода пара. Перепуск части пара между ступенями одного из цилиндров осуществляют, когда контролируемое соотношение осевых усилий роторов цилиндров превысит определенное установленное значение. При этом, если уменьшают расход пара через один из цилиндров, перепуск части пара осуществляют между ступенями другого цилиндра, а, если расход пара увеличивают через один из цилиндров, перепуск части пара осуществляют в этом же цилиндре. Такой способ, обеспечивая защиту упорного подшипника от перегрузки, является более простым в реализации и вместе с тем не оказывает влияния на экономические характеристики работы паровой турбины. 1 ил.

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10-01-2006 дата публикации

СЕРВОМОТОР БЛОКА РЕГУЛИРУЮЩИХ КЛАПАНОВ ТУРБИНЫ

Номер: RU2004116414A
Принадлежит:

... 1. Сервомотор блока регулирующих клапанов паровой турбины, содержащий два штока, первый из которых проходит через корпус сервомотора в его нижней части и непосредственно соединен со штоком нижнего клапана, второй шток жестко соединен с осью рычажной передачи, связанной со штоком верхнего клапана, в полости слива корпуса концентрично установленные возвратные наружная и внутренняя пружины, опертые соответственно в поршень сервомотора и противостоящую ему тарелку, отличающийся тем, что второй шток выполнен полым, внутри него проходит первый шток, выходящий вместе со вторым в верхней части корпуса, полый шток соединен с поршнем сервомотора, на первом штоке в сливной полости установлена посредством шпонки тарелка с обеспечением взаимодействия поршня с тарелкой, при этом ось рычажной передачи размещена в сквозном пазу первого штока с зазором относительно паза с обеспечением взаимодействия штоков и гарантированного закрытия клапанов, полый шток имеет противолежащие прорези в месте установки тарелки ...

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27-07-2012 дата публикации

СЕРВОМОТОР ДЛЯ ПРИВОДА РЕГУЛИРУЮЩЕГО КЛАПАНА ПАРОВОЙ ТУРБИНЫ

Номер: RU2011103142A
Принадлежит:

Сервомотор для привода регулирующего клапана паровой турбины, включающий силовой цилиндр с поршнем, нагруженным пакетом пружин, и штоком, соединенным с регулирующим клапаном и золотниковым устройством, в котором размещены неподвижная и подвижная буксы с окнами, золотник, с одной стороны нагруженный импульсным давлением от управляющего блока системы регулирования турбины, а с другой стороны - золотниковой пружиной, к золотниковому устройству присоединены маслопровод управляющего масла, соединенный посредством отверстий в подвижной буксе с верхней торцевой камерой, и маслопровод напорной магистрали, соединенный с золотниковым устройством, отличающийся тем, что золотниковая пружина размещена вне корпуса золотникового устройства в боксе, образованном корпусом с дренажным трубопроводом и съемной крышкой, прикрепленными к нижнему фланцу золотникового устройства так, что одна часть бокса закрыта сверху золотниковым устройством, а другая - съемной крышкой, при этом внутри бокса расположен равноплечий ...

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20-08-2013 дата публикации

ПРИВОДНАЯ СИСТЕМА ДЛЯ ПОДВИЖНОГО ЭЛЕМЕНТА ГОНДОЛЫ ДВИГАТЕЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА, ТАКОГО КАК ЗАСЛОНКА РЕВЕРСОРА ТЯГИ

Номер: RU2012103713A
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... 1. Система для приведения в действие по меньшей мере одного элемента гондолы летательного аппарата, содержащая по меньшей мере два привода (А1, А2, A3), соединенные друг с другом кинематическим образом, первичную схему (1) генерации гидравлической (соответственно, электрической) энергии, выполненную с возможностью управления по меньшей мере одним (А1) из указанных двух приводов, и вторичную схему (13) генерации электрической (соответственно, гидравлической) энергии, выполненную с возможностью управления другим приводом (A3).2. Система по п.1, в которой указанные приводы (А1, А2, A3) являются механическими, причем указанная первичная схема (1) использует гидравлическую энергию, воздействующую на гидродвигатель (М1), действующий на один (А1) из приводов, а указанная вторичная схема (13) использует электрическую энергию и содержит электродвигатель (М13), действующий на гидравлический насос (Р), который в свою очередь воздействует на гидродвигатель (М133), действующий на другой привод (A3).3 ...

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15-05-1993 дата публикации

LOAD CONTROL METHOD FOR MULTICYLINDER REGENERATIVE-EXTRACTION STEAM TURBINE

Номер: RU1815336C
Автор:
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23-10-1987 дата публикации

Способ регулирования тепловой нагрузки теплофикационной турбоустановки

Номер: SU1346824A2
Принадлежит:

Изобретение позволяет повысить экономичность работы турбины с производственным отбором пара из камеры перед парораспределительными органами части среднего давления. При достижении парораспределительными органами 4 части среднего давления максимального открытия разрыв цепи управления электроприводами задвижки 11 или задвижек 15, 16 и 21 через элемент ИЛИ 38 выключателем 35 происходит до достижения ими заданного положения . Это положение соответствует полному или частичному отключению регенеративных подогревателей. Отбор пара на производство осуществляется по трубопроводу 39. В результате предотвращаются повышение давления в камере производственного отбора и снижение мощности турбины. 1 ил. г /п/)2 ,--i I 35 L ,1 g Jvl35 I . Г л J fl JlfiJQLQl 3J t 32L33JL 26 L.SL4.4i -- I;i:ii.z j т123 (Л ,-6 I со о: 00 ю 4: ISJ ...

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07-10-1987 дата публикации

Система регулирования тепловой нагрузки турбины

Номер: SU1343037A1
Принадлежит:

Изобретение позволяет повысить надежность турбины. Для этого выхода 15 Больше регулятора 11 располагаемой тепловой нагрузки подключен к входу управляемого контакта 13 релейного элемента 14, а через него и привод 5 - с выходом 12 Больше регулятора 9 потребляемого тепла. При устранении причины, вызвавшей недопустимое увеличение тепловой нагрузки турбины, и уменьшении в результате этого мощности предотборного отсека до величины, меньшей минимальной, на выходе 15 появляется сигнал, вызывающий срабатывание элемента 14 и замыкание контакта 13. Сигнал с выхода 12 поступает на вход 6 Открыто . привода 5 регулирующего органа 4. При этом значение параметра, задаваемого тепловым потребителем, увеличивается и одновременно уменьшается запас по мощности предотборного отсека. Этот процесс продолжается до тех пор, пока значение теплового параметра станет равным заданному или мощность предотборного отсека примет значение, равное минимальному значению. 2 ил. П i (Л IS э-та 12 Оэ 4 со о со 001. Т Пар ктеnjiotpfiunoтревителп ...

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28-02-1934 дата публикации

Устройство для регулирования двух вальных паровых турбин

Номер: SU34558A1
Автор: Снедков А.П.
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09-08-1971 дата публикации

Способ регулирования теплофикационной турбины

Номер: SU311015A1
Автор: Сорокин А.И.
Принадлежит:

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15-04-1966 дата публикации

Способ регулирования турбин

Номер: SU181136A1
Принадлежит:

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30-11-1987 дата публикации

Устройство для определения нечувствительности системы регулирования турбины

Номер: SU1355732A1
Принадлежит:

Изобретение позволяет повысить надежность устр-ва. Измерительная часть устр -ва содержит датчики 1 и 2 частоты вращения ротора турбины и положения регулирующих клапанов с соответствующими цифровыми преобразователями 3 и 4,-подключенными к цифропечатающему регистратору . Управляющая часть устр-ва содержит логический элемент 5, подключенный к программному блоку 6 и связанный с выходом прербразова- теля 3; Выход блока 6 соединен с входом преобразователя 3 непосредственно , а с входом преобразователя 4 через блок 7 запаздывания. Измерение производится автоматически через заданный интервал изменения частоты вращения ротора турбины, а число измерений при различных темпах изменения частоты вращения во время определения нечувствительности системы регулирования может быть выдержано, оптимальным. 1 ил i (Л со сл С71 | 00 ю к ци(рдопечотающема регистратору ...

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07-03-1987 дата публикации

Система регулирования турбины

Номер: SU1295012A1
Принадлежит:

Изобретение относится к теплоэнергетике и позволяет повысить надежность регулирования . Система содержит формирователь 1 заданной мощности, ограничитель 2, выявитель 3 минимального сигнала ограничения , датчик 4 давления пара перед турбиной , формирователь 5 поправки заданной мощности по давлению, датчик 6 и задат- чик 8 частоты вращения ротора турбины. формирователь 7 сигнала рассогласования по частоте, сумматоры 9, 14, датчик 10 мощности , блок управления, многорежимный интегратор 12 и многоканальный коммутатор 13. Система обеспечивает автоматический выбор режима регулирования по иерархии и формирование управляющего сигнала согласно заданным алгоритмам, формирователь поправки заданной мощности по давлению в зависимости от выбранного режима регулирования давления (астатический режим поддержания величины давления в момент включения режима, стерегущий режим поддержания минимальной уставки давления, режим регулирования давления и мощности по статической характеристике давление- мощность) ...

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07-01-1987 дата публикации

Способ регулирования отбора пара из турбины

Номер: SU1281685A1
Принадлежит:

Изобретение относится к теплоэнергетике и позволяет повысить надежность . Регулирование производится воздействием на приводы обратного 3 и регулирующего 4 клапанов, установленных на трубопроводе 2 отбора пара из турбины. При увеличении тепловой нагрузки потребителя, что проявляется в понижении давления пара за кла-. паном 4 ниже заданного значения, дросселирование отбираемого пара осуществляется только в этом клапане . При включении привода 5 клапана 3 в режиме максимального отбора пара на последнем возникает перепад давлений , который измеряется. При венстве этого перепада перепаду давлений на клапане 4 в режиме минимального отбора пара находят некоторое положение клапана 4. При отклонении положения последнего от найденного в сторону .его закрытия воздействуют на привод 5 в сторону его закрытия При полном открытии клапана 4 это воздействие снимают. 1 ил. I (Л к: 00 а 00 сд ...

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15-05-1984 дата публикации

Система регулирования теплофикационной паротурбинной установки

Номер: SU1092284A2
Принадлежит:

СИСТЕА А РЕГУЛИРОВАНИЯ ТЕПЛОФИКАЦИОННОЙ ПАРОТУРБИННОЙ УСТАНОВКИ, по авт. св. № 994783, отличающаяся тем, что, с целью расошрения диапазонов регулирования тепловой и электрической нагрузок, в систему введены дифференциатор и инерционный элемент, один вход которого соединен с выходом регулятора тепловой нагрузки, второй вход соединен через дифференциатор с датчиком давления пара в отборе на сетевой подогреватель , а выход подключен ко входу механизма управления турбиной. (Л со o ю оо ...

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07-12-1983 дата публикации

Гидравлическая система управления

Номер: SU1059291A1
Принадлежит:

... 1. ГИДРАВЛИЧЕСКАЯ СИСТЕМА УПРАВЛЕНИЯ, например, паротурбинной установки, содержащая насос, сообщенный с исполнительным устройством, снабженным дроссельными элементами типа сопло-заслонка , расположенными в дренажной камере, и бак, сообщенный с дренажной камерой , отличающаяся что, с целью повышения надежности, она снабжена генератором паромасляной смеси, подключенным к насосу параллельно исполнительному усуройству и сообщенным своим выходом с дренаж юй камерой. 2. Система по п. 1, отличающаяся тем чтоПгенератЬр паромасля|(ой смеси снабжен последовательно установленными между нинс и насосом устройством для вакуумйрова-, ни я рабочей жидкости и нагревателем и установленным между генератором и дренажной камерой ресивером, дополнительно сообщенным с генератором байпасной линией . З Система по пп. 1, 2, отличающаяся тем,чт,о на входе генератора паромасляиой смеси установлен регулятор расхода.

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30-01-1984 дата публикации

Система регулирования теплофикационной паротурбинной установки

Номер: SU1070250A1
Принадлежит:

СИСТЕМА РЕГУЛИРОВАНИЯ ТЕПЛОФИКАЦИОННОЙ ПАРОТУРБИННОЙ УСТАНОВКИ, содержащая регулятор мощности, выход которого соединен с сервомотором клапанов части высокого давления турбины и с входом регулятора давления , подсоединенного также своим входом к регулятору тепловой нагрузки, а выходом - к приводу байпасного клапана на линии обвода сетевых подогревателей, отличаю щаяся тем, что, с целью повыщения надежности и маневренности установки с двухступенчатым подогревом сетевой воды в первом и втором сетевых подогревателях, подключен ных соответственно к верхнему и нижнему отборам пара из турбины и снабженных линией обвода второго подогревателя с байпасным клапаном и приводом этого клапана, путем оптимизации распределения тепловой нагрузки между подогревателями, в нее введены нелинейный элемент, сумматор, датчик давления пара в нижнем отборе и задатчик максимального значения этого давления , подключенные через нелинейный элемент к входу сумматора, и выход регулятора давления дополнительно подсоединен ...

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07-12-1984 дата публикации

Устройство для определения технического состояния системы регулирования турбоагрегата

Номер: SU1127980A1
Принадлежит:

УСТРОЙСТВО ДЛЯ ОПРЕДЕЛЕНИЯ ТЕЖИЧЕСКОГО СОСТОЯНИЯ СИСТЕМЫ РЕГУЛИРОВАНИЯ ,ТЭТВОАГРЕГАТА, содержащее датчик яолокения сервомото ,ра р.егулирукщих клапанов, подключенный к входу регистратора,датчик входного сигнала,/ генератор щжмоугольных . импульсов и снабженный,. управлякощми койтактами и ключом механизм управления трубодгрега том,, подключеншле к входу блока регулирования, и-блок ЭТФавления, подключенный к генератору прямоугольных импульсов, регистратору и механизму управлешш, о т лич а е е с я тем, что,с . целью повышения оперативности онредеяения технического состойния оно снабжено эадатчиком норьвфованного сигнала, вьаюлнённого в виде реле времени с контактами, включенными последовательно с;управлякшщми контактами июшчом мемеханизма этФавяеяия.

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07-12-1984 дата публикации

Способ регулирования паровой турбины

Номер: SU1127981A1
Принадлежит:

СПОСОБ РЕГУЛИРОВАНИЯ ПАРОВОЙ ТУРБИЙЫ с генератором, работающим в энергосистеме, путем формирования управляющих воздействий на сервомотор турбины по заданным значениям положения сервомотораj мощности и степени статизма с учетом обратных связей по фактическим положению сервомотора и мощности, изме рения скорости изменения MOBQIOCTH турбины и сравнения этой скорости с порогоньЕм значёнкем, JO т л я ч аю щ и и с я тем, то, с целью повышения надежности турбины и увеличения выработю алектроэнергии, после превьшеяня скоростыо изменения мопцюсти порогового 9начен1{я формирование у11равпя{ощих воздействий ведут по пропорционадьяо-интегральнсжу . закону отключают обратную связь по мощности, понижают степень статизма и после вь(цержки вр&4ени и при . отсутствии в заданного интервала времеш иревишеаия средним, значением мощости пороговой величины задают волояеение сервомотора соотвётствукшрш собственным нухдам турбины. .

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30-08-1984 дата публикации

Устройство для управления мощностью турбины

Номер: SU1110911A1
Принадлежит:

УСТРОЙСТВО ДЛЯ УПРАВЛЕНИЯ МОЩНОСТЬЮ ТУРБИНЫ, содержащее блок запоминания с управляющим и информационным входами, последний из которых подключен к датчику мощности, формирователь заданной мощности, под . ключенный к первому входу ограничителя, ко второму входу которого подключен выявитель минимального сигнала, соединенный своими входами с датчиками ограничительных сигналов и с выходом первого переключателя , имеющего управляющий и информационные входы, последние из которых I подключены к выходам блока запоминания и формирователя аналоговых сигналов, и второй переключатель с управляющими и информационными входами, отличающееся тем, что, с целью расширения функциональных возможностей при управлении по командам датчиков энергосистемной автоматики, в устройство введены вычитатель и элемент ИЛИ, подключенный своими входами к датчикам энергосистемной автоматики, а выходом - к управляющим входам блока запоминания и первого переключателя, вычитатель включен в линию соединения входа выявителя минимального ...

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07-01-1989 дата публикации

Устройство для управления мощностью турбины

Номер: SU1449668A1
Принадлежит:

Изобретение позволяет расширить функциональные возможности управления мощностью турбины по командам датчиков энергосистемной автоматики и повысить помехозащищенность. Для управления мощностью турбины выходной сигнал ограничителя 13 формируется подачей на его входы сигнала заданной мощности от формирователя 14 и сигнала от выявителя 12 минимального сигнала, получающего информацию от- датчиков ограничительных сигналов и от выявителя 11 максимального из двух сигналов - от вьиитателя 10 и от блока 1 формирователя аналоговых сигналов и первого и второго блоков 6 и 7 запоминания, связанных с переключателями 8 и 9. Блок 4 управления получает воздействия от датчиков энергосистемной автоматики через элемент ИЛИ 3 и через иерархический блок 2 элементов памяти и при своем срабатывания воздействует на управ- ляюпще входы переключателей 8 и 9. Переключатель 5 пропускает только один из сигналов датчиков энергосистемной автоматики на вход вычитате- ля 10. Иерархический блок 2 элементов памяти организует ...

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23-02-1993 дата публикации

Система регулирования и защиты паровой турбины

Номер: SU1797671A3

Использование: автоматическое регулирование и защита энергетических паровых турбин. Сущность изобретения: масло подведено через межпрясковые полости и окно в межпоясковую полость. Под действием его давления подвижная букса находится на упоре в буртик цилиндрического отростка золотника и сжимает пружину. Надпоршне- вая камера окном в дифференциальном отростке поршня соединена с межлояско вой полостью и подпоршневой камерой. Датчик (Д) электрической нагрузки генератора подключен к шинам последнего, D положения и размыкатель кинематически связаны попарно с регулирующим BWHTOM (РВ) и поршнем сервомотора. Сигналы (С) датчиков подведены на вход сумматора, результирующий С которого подведен напрямую на электромагнит через размыкатель и реле времени - на другой электромагнит. 2 з. п. ф-лы, 1 ил.- . ел ...

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17-04-1975 дата публикации

Номер: DE0002333525B2

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14-04-1930 дата публикации

Regelungsvorrichtung fuer Kraftmaschinen, insbesondere fuer Turbinen

Номер: DE0000495960C
Автор:
Принадлежит: HENRY HEILEMAN WAIT

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14-03-1984 дата публикации

STEAM TURBINE CONTROL

Номер: GB0002084260B
Автор:
Принадлежит: GEN ELECTRIC, GEC US

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17-09-1975 дата публикации

SPEED CONTROL SYSTEM FOR A VAPOUR ENGINE

Номер: GB0001406659A
Автор:
Принадлежит:

... 1406659 Automatic control of speed THERMO ELECTRON CORP 6 Dec 1972 [6 Jan 1972] 56227/72 Heading G3R The speed of a vapour engine expander is controlled by means of a stepping motor actuated throttle valve supplied with pulses at a rate which is proportional to a speed error signal derived from comparison of the actual speed of the expander and the desired speed. The expander 13 of vapour engine plant 11 drives an alternator 35 whose output is used as a speed signal and is shaped to produce a squarewave signal at 37. A monostable multi-vibrator 39 is triggered by the squarewave signal to produce standard length reference pulses which open gate 41 to allow capacitor Cl to charge positively and the squarewave signal pulses after inversion open gate 53 to charge capacitor Cl negatively. The voltage on capacitor Cl thus represents the speed error and its polarity the direction in which the error exists (i.e. fast or slow). The polarity is used to set circuits 33 controlling the selection of ...

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02-05-1962 дата публикации

Improvements in expansion turbines

Номер: GB0000895166A
Автор:
Принадлежит:

... 895,166. Elastic-fluid turbines. LAWS, P. Aug. 25, 1959 [Aug. 25, 1958], No. 27251/58. Class 110 (3). An outward radial flow turbine comprises an output shaft 1 and a hollow shaft 43 aligned with the output shaft and constituting an inlet duct for motive fluid such as steam, at least one hollow arm 50 extending radially of the shafts and connected to rotate therewith, the arm communicating with the interior of the hollow shaft and having at its outer end an expansion nozzle 52, a ring of fixed blades 58 being located so as to receive motive fluid discharged from the nozzle or nozzles and to re-direct it on to a set or sets of rotor blades 68 mounted on a rotor disc 64 radially outwardly of the nozzle or nozzles. The hollow shaft 43 is formed with a flange 47 which is received in a recess in a hub member 44, the latter abutting against the rotor disc 64. A flange 45 formed at the upper end of the output shaft 1 abuts against the other face of the rotor disc 64, and a flange member 85 abuts ...

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15-08-1986 дата публикации

ADJUSTMENT DEVICE FOR THE GUIDE VANES OF AN AXIAL TURBOMACHINE.

Номер: AT0000021435T
Автор: FALTYS JAN, FALTYS, JAN
Принадлежит:

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13-01-2011 дата публикации

ACTUATING SYSTEM FOR A MOVABLE AIRCRAFT ENGINE NACELLE ELEMENT, SUCH AS A THRUST REVERSER COVER

Номер: CA0002765217A1
Принадлежит:

Ce système d'actionnement d'au moins un élément de nacelle d'aéronef comprend au moins deux actionneurs (A1, A2, A3) reliés cinématiquement entre eux, un circuit principal (1 ) à génération hydraulique (respectivement électrique) apte à commander au moins l'un (A1 ) des deux actionneurs, et un circuit secondaire (13) à génération électrique (respectivement hydraulique) apte à commander l'autre actionneur (A3).

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04-08-2005 дата публикации

DUAL RETENTION VANE ARM

Номер: CA0002486587A1
Принадлежит:

A variable vane arm is disclosed having dual retention capability to ensure vanes of a gas turbine engine remain connected to the vane arm even under surge loads or when fastener preload, or the entire fastener, is lost. The variable vane arm further provides a surge slot to facilitate rotation of the vane even when the vane is operating under surge or otherwise excessively high pressure conditions.

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20-06-2017 дата публикации

METHOD FOR DETECTING A VALVE FAILURE IN A TURBOSHAFT ENGINE

Номер: CA0002953872C
Принадлежит: SAFRAN AIRCRAFT ENGINES

L'invention concerne un procédé de surveillance d'une vanne dans un turbomoteur, ladite vanne commutant en réponse à une commande (C) envoyée à un instant déterminé (t0), ledit procédé comportant une étape (E2) de calcul d'une première forme (SI) d'un signal temporel (S(t)) à partir de l'évolution d'une variable d'état (P) dudit turbomoteur réagissant à une commutation de ladite vanne, puis une étape (E6) d'application d'un test de signature de la commutation de la vanne à une deuxième forme (S2) dudit signal (S(t)), caractérisé en ce que ledit procédé comporte une étape (E5), dite de désensibilisation, dans laquelle ladite deuxième forme du signal (S2) est calculée à partir de la première forme (SI) du signal.

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05-07-2016 дата публикации

SYSTEM FOR CONTROLLING VARIABLE GEOMETRY EQUIPMENT FOR A TURBINE ENGINE, ESPECIALLY BY BELLCRANKS

Номер: CA0002738211C
Принадлежит: SNECMA

Système de commande d'au moins deux équipements (10, 110) à géométrie variable d'une turbomachine, la turbomachine comportant au moins un premier corps et un deuxième corps, le premier équipement (10) étant un étage d'aubes de stator à angle de calage variable d'un compresseur du premier corps évoluant entre une position fermée au ralenti et une position ouverte à fort régime, le second équipement (110) étant au moins une vanne de décharge d'un compresseur du deuxième corps évoluant entre une position ouverte au ralenti et une position fermée à fort régime. L'actionneur entraîne le second équipement (110) par l'intermédiaire d'une pièce d'actionnement (65) qui est actionnée sur une partie de la course de l'actionneur et au repos sur une butée (64) sur le reste de la course, et par l'intermédiaire d'un organe de jonction coulissant (120) ménageant une course morte dans l'actionnement dudit second équipement.

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14-05-1976 дата публикации

Номер: CH0000575544A5
Автор:

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14-11-1986 дата публикации

STEAM TURBINE POWER STATION AS WELL AS A PROCEDURE FOR ITS ENTERPRISE.

Номер: CH0000658493A5
Принадлежит: GEN ELECTRIC, GENERAL ELECTRIC COMPANY

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14-08-1987 дата публикации

AXIAL TURBOMACHINE.

Номер: CH0000661772A5
Автор: FALTYS, JAN
Принадлежит: ESCHER WYSS AG, SULZER-ESCHER WYSS AG

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15-07-2016 дата публикации

turbine systemramp rates during the operation of a system for providing variable.

Номер: CH0000710617A2
Принадлежит:

Ein System (10) schliesst eine Steuerungseinrichtung (38) ein, die dazu eingerichtet ist, eine oder mehrere Eingaben zu empfangen, die einem Betrieb eines Turbinensystems (12) zugeordnet sind, einen Satz von Rampenraten für das Gasturbinensystem (12), basierend wenigstens teilweise auf den einen oder mehreren Eingaben abzuleiten und eine Rampenrate aus einer Menge von Rampenraten auszuwählen. Die Rampenrate schliesst eine variable Rampenrate ein. Die Steuerungseinrichtung (38) ist weiter dazu eingerichtet, ein Ausgangssignal, basierend auf der ausgewählten Rampenrate, zu erzeugen.

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15-02-2003 дата публикации

СИСТЕМА АВТОМАТИЧНОГО РЕГУЛЮВАННЯ УПРАВЛІННЯ ПАРОВОЮ ТУРБІНОЮ

Номер: UA0000054347 A

Система автоматичного регулювання управління паровою турбіною включає вплив тиском масла від насоса на регулятор швидкості і золотник керування сервоприводом регулюючих клапанів турбіни. Вплив тиском масла від насоса здійснюють безпосередньо на золотник керування спеціальним пневматичним клапаном - регулятором швидкості, що автоматично управляється сигналом з комп'ютера.

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20-09-1963 дата публикации

Mode of regulation of the turbo-compressors of overfeeding and device of implementation

Номер: FR0001337864A
Автор:
Принадлежит:

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23-04-1956 дата публикации

Regulator for turbines, in particular for steam turbines ordered by oil

Номер: FR0001115349A
Автор:
Принадлежит:

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25-01-1909 дата публикации

Improvements to the regulatory mechanism of elastic fluid turbines

Номер: FR0000394464A
Автор:
Принадлежит:

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19-03-1982 дата публикации

PROCEDE ET SYSTEME DE COMMANDE D'UNE TURBINE A VAPEUR

Номер: FR0002490273A
Принадлежит:

PROCEDE PERMETTANT D'AUGMENTER LA PRESSION LORSQUE LE DEBIT S'ACCROIT. IL CONSISTE: -A MESURER LA PRESSION DANS LE COLLECTEUR DE VAPEUR 51; -A OUVRIR LA VANNE DE DERIVATION (HPBP) POUR UNE VALEUR DE REFERENCE DE PRESSION PLANCHER; -A OUVRIR LA VANNE DE REGLAGE PRINCIPALE (MCV) POUR UNE COMMANDE VITESSECHARGE; -A FERMER LA VANNE DE DERIVATION POUR MAINTENIR LA PRESSION DE VAPEUR DU COLLECTEUR A LA VALEUR DE REFERENCE LORSQUE LA VANNE DE REGLAGE PRINCIPALE S'OUVRE; -A PASSER DE LA COMMANDE DES PARAMETRES VITESSECHARGE A LA COMMANDE DE LA PRESSION; A OUVRIR SUR DE PLUS GRANDES VALEURS D'OUVERTURE LA VANNE DE REGLAGE PRINCIPALE AFIN DE MAINTENIR LA PRESSION DE VAPEUR DU COLLECTEUR A LA VALEUR DE REFERENCE A MESURE QUE LE DEBIT DE VAPEUR S'ACCROIT; -A COMPARER LA POSITION DE LA VANNE DE REGLAGE PRINCIPALE A UNE VALEUR DE REFERENCE DE MARGE DE POSITION DE CETTE VANNE; -A AJUSTER LA VALEUR DE REFERENCE DE PRESSION POUR MAINTENIR LA POSITION DE LA VANNE DE REGLAGE PRINCIPALE A LA VALEUR D'OUVERTURE ...

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24-07-2015 дата публикации

CONTROL SYSTEM FOR VARIABLE GEOMETRY EQUIPMENT OF A TURBOMACHINE, ESPECIALLY BY BELLCRANKS.

Номер: FR0002936556B1
Принадлежит: SNECMA

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07-11-1975 дата публикации

ADJUSTABLE STATOR VANE ASSEMBLY

Номер: FR0002267454A1
Автор:
Принадлежит:

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14-01-2011 дата публикации

SYSTEM Of ACTUATION FOR VARIABLE COMPONENT OF NACELLE OF ENGINE Of AIRCRAFT, SUCH AS a CAP Of Thrust reverser

Номер: FR0002947870A1
Принадлежит: AIRCELLE

Ce système d'actionnement d'au moins un élément de nacelle d'aéronef comprend au moins deux actionneurs (A1, A2, A3) reliés cinématiquement entre eux, un circuit principal (1) à génération hydraulique (respectivement électrique) apte à commander au moins l'un (A1) des deux actionneurs, et un circuit secondaire (13) à génération électrique (respectivement hydraulique) apte à commander l'autre actionneur (A3).

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31-01-1975 дата публикации

Hydraulic guide-wheel adjusting mechanism

Номер: FR0002236083A1
Автор:
Принадлежит:

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19-03-1982 дата публикации

PROCESS AND CONTROL DEVICE Of a STEAM TURBINE

Номер: FR0002490273A1
Принадлежит:

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18-09-1908 дата публикации

Improvements to regulatory mechanisms for elastic fluid turbines

Номер: FR0000389753A
Автор:
Принадлежит:

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26-10-2020 дата публикации

METHOD FOR TESTING QUICK CLOSING OF ACTUATOR FOR POWER PLANT

Номер: KR0102169666B1
Автор:
Принадлежит:

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29-03-2018 дата публикации

제어 장치, 시스템 및 제어 방법

Номер: KR0101843698B1

... 흡입한 공기를 압축기에 의해 압축해서 압축 공기로 하고, 연소기로부터 공급된 연료와 상기 압축 공기를 혼합해서 연소시킴으로써 연소 가스를 생성하고, 생성한 상기 연소 가스에 의해 터빈을 작동시켜 로터를 회전시키고, 상기 터빈을 작동시킨 상기 연소 가스를 배기 가스로서 배출하는 가스 터빈의 제어 장치(14)로서, 압축기는 흡기측에 마련되는 개방도를 조정 가능한 입구 안내 날개를 갖고, 가스 터빈의 부하에 따라서 규정되는 배기 가스 온도의 상한 온도인 온도 조정선을 따라서, 입구 안내 날개의 개방도를 제어하는 온도 조정 제어를 실행하고, IGV 개방도 지령값은 가스 터빈의 출력 디맨드에 근거해서 설정된다.

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12-03-2015 дата публикации

GAS TURBINE PLANT, CONTROL DEVICE THEREOF, AND GAS TURBINE OPERATION METHOD

Номер: WO2015033769A1
Принадлежит:

This control device (50) is provided with: a temperature control unit (51) which controls the degree of opening of a fuel flow regulator valve (47) so as to maintain the inlet of a turbine (21) into which a fuel gas enters at a constant temperature; and an air intake control unit (52) which receives from a calorimeter (55) the unit amount of heat of fuel supplied to a combustor (19) and controls an air intake regulator (15) such that the air intake amount in an air compressor (11) changes in positive correlation to changes in the unit amount of heat.

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06-03-2003 дата публикации

SYSTEM AND METHOD FOR PROVIDING BALLAST LOADING FOR A TURBO-GENERATOR

Номер: WO2003019767A1
Принадлежит:

A ballast load (38) control system and method is presented that regulates the output electrical power supplied by a turbo-generator (18) such that appropriate turbine loading may be achieved. Such enables the use of a turbo-generator (18) having an expansion turbine to be used to provide a controlled, required amount of cooling to a thermal control system. By effectively varying the coupled electrical load (38, 40), the loading provided to the expansion turbine may be controlled while maintaining output power requirements to connected electrical utilization equipment. Use of a common system controller (22) for both the cooling system and ballast trim load system of the present invention ensures coordinated operation between the required amount of cooling and electrical power quality supplied to the coupled utilization equipment.

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20-02-1923 дата публикации

Power generator

Номер: US1446084A
Автор:
Принадлежит:

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06-03-2014 дата публикации

SYSTEM AND METHOD TO ALIGN VARIABLE DIFFUSER VANE WITH DIRECTION OF FLOW OF WORKING FLUID

Номер: US20140064921A1
Принадлежит: Dresser Inc.

Embodiments of systems and methods permit use of variable diffuser vanes in multi-stage compressor devices. These embodiments deploy a flow sensor to identify the direction of flow for a working fluid that transits the stages of the compressor device. In one embodiment, the flow sensor generates a signal, which a controller processes to align a variable diffuser vane with the direction of flow of the working fluid. This configuration pre-empts the operational difficulties of previous designs by providing independent control over the diffuser vanes in the individual stages of the multi-stage compressor device.

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16-11-2016 дата публикации

EMBEDDED SENSOR SYSTEM

Номер: EP3093800A1
Принадлежит:

A magnetic communication system for a gas turbine engine (10) may include a sensor (42) coupled (58) to a microcontroller (43). A low frequency radio-frequency identification integrated chip (44) may be coupled (60) to the microcontroller. A first coupling circuit (62) may be coupled (78, 82) to the low frequency radio-frequency identification integrated chip and may include a first coil winding (90) wound within a first core (39). The first coil winding may be operatively associated with a low frequency magnetic flux.

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01-05-2019 дата публикации

Systems and methods involving multiplexed engine control signals

Номер: EP2128405B1
Автор: Cloft, Thomas G.
Принадлежит: United Technologies Corporation

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16-11-1977 дата публикации

Номер: JP0052151202U
Автор:
Принадлежит:

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27-10-1983 дата публикации

Номер: JP0058501829A
Автор:
Принадлежит:

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23-01-1988 дата публикации

SPEED CONTROL DEVICE OF TURBINE

Номер: JP0063016104A
Автор: TOMINAGA NORIAKI
Принадлежит:

PURPOSE: To protect a turbine from its stopping due to trouble in speed detection system, by setting up electromagnetic pickups and detectors, as many as more than four, and selecting signals of the speed detectors signal selection circuit. CONSTITUTION: Respective electromagnetic pickups 4 and the speed controller 5 through a signal selection circuit 11. The signal circuit 11 selects the second higher one, when four detection signals are output, and when two out of four are feeding output OV the higher one out of two is selected. Even if 3 out of 4 are in trouble, controlling can be achieved with only one detection signal. COPYRIGHT: (C)1988,JPO&Japio ...

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11-04-1986 дата публикации

Номер: JP0061013118B2
Принадлежит:

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14-04-1989 дата публикации

CONTROL METHOD FOR TOTAL FLOW TURBINE

Номер: JP0001096404A
Автор: ONO YOSHIICHI
Принадлежит:

PURPOSE: To facilitate control of output and rotation by making hot water flow ejected through a nozzle constant and regulating steam flow flowing directly to a rotor vane without passing through the nozzle by means of a regulation valve. CONSTITUTION: Geothermal steam taken from a geothermal well 1 is fed to a separator 2 where it is depressurized and separated into steam and hot water. Hot water is fed through a hot water conduit 13 to a nozzle box 11 and ejected through a nozzle 8 to a flow path 12 of a rotor blade 9 where it is flushed to produce accelerated two-phase flow which is ejected to the outside of the rotor vane 9. Then it is fed through a steam conduit 14 between a casing 6 and the nozzle box 11 from where it is fed to a labylinth section 7. Quantity of steam to be consumed for sealing is regulated through regulation of the opening of a regulation valve 15 and the steam is fed directly to the rotor vane 9. Since the quantity of steam to be mixed with hot water in the way ...

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24-05-1985 дата публикации

CONTROL APPARATUS FOR STEAM TURBINE

Номер: JP0060093104A
Автор: SHINDO KURA
Принадлежит:

PURPOSE: To prevent the output variation in valve test by providing a reference load setter in individual one of a plurality of steam turbines and changing the reference loads of the turbine subjected to the valve test and other ones to send a certain amount of electric power to a main system. CONSTITUTION: In a control unit for steam turbines 4, 104 which drive a plurality of generators 5, 8 for supplying electric power to a main system 10, the signals of a charging amount setter 144 and a charging amount detector 161 are sent to the input of a comparator 143. The signal from a load rate bias circuit 142 is added to and subtracted from the deviation signal of the comparator by adders 202a, 202b to generate the reference load setting signal of each turbine. When a switch 140 is turned off in the valve test to set any load rate by a bias circuit 142, a valve for one turbine is closed. And the valve opening of the other turbine is increased, and an adding and subtracting valve can be tested ...

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09-10-1995 дата публикации

Номер: JP0007091963B2
Автор:
Принадлежит:

Подробнее
31-08-1976 дата публикации

VAPOR ENGINE SPEED CONTROL

Номер: CA996236A
Автор:
Принадлежит:

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31-07-1984 дата публикации

STEAM TURBINE CONTROL

Номер: CA1171671A
Принадлежит: GEN ELECTRIC, GENERAL ELECTRIC COMPANY

... 17MT-2786 STEAM TURBINE CONTROL In a power plant which includes a steam turbine with main control valves for admitting steam into steam turbine and a steam bypass with bypass control valves for diverting steam around the steam turbine directly into a condenser, it is necessary to coordinate the operation of the respective valves so that the steam turbine can be started, brought up to speed, synchronized with a generator and then loaded as smoothly and efficiently as possible. The present invention provides for such operation and, in addition, allows for the transfer of power plant operation from the so-called turbine following mode to the boiler following mode through the use of the sliding pressure concept. The invention described is particularly applicable to combined cycle power plants.

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26-02-1980 дата публикации

INSTALLATION FOR CONTROLLING PRESSURE OF GAS UNDER SHAFT TOP IN SUPER-CAPACITY BLAST FURNACE

Номер: CA1072656A

Installation includes a throttle assembly built in the blast-furnace outlet pipe and at least two gas turbines with blast-furnace gas heaters also built in the outlet pipe in parallel with the throttle assembly. Each of the gas turbines having a control diaphragm and a stop diaphragm is provided with a separate drive for turning thereof. The installation is also furnished with an isodromic regulator for the gas pressure under the shaft top of the blast-furnace electrically connected to the separate drives of the throttles being a part of a throttle unit and by means of a logic control unit also connected to separate drives of the control diaphragms of the gas turbines it preselects such a sequence of operation of the above drives when in the process of the gas pressure control under shaft top in supercapacity blast furnace to open in the first-turn the control diaphragms of the gas turbines and then to open the throttles which being a part of the throttle assembly. But when closing the ...

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22-04-1980 дата публикации

ENGINE CONTROL SYSTEM

Номер: CA0001075918A1
Принадлежит:

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26-05-2020 дата публикации

RELATIVE POSITION MEASUREMENT

Номер: CA0002932599C
Принадлежит: GEN ELECTRIC, GENERAL ELECTRIC COMPANY

A feedback sensor system is provided. The feedback sensor system includes a first ring rotatable about an axial direction and a second ring also rotatable about the axial direction. The first ring includes one or more first ring features and the second ring includes one or more second ring features. The feedback sensor system also includes a sensor directed at the surface of the first ring for sensing a parameter influenced by the one or more first ring features and the one or more second ring features. The sensor may determine a position of the first ring relative to the second ring by sensing the parameter.

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17-02-2003 дата публикации

SYSTEM FOR AUTOMATED ADJUSTMENT OF STEAM TURBINE CONTROL

Номер: UA0000054347C2
Автор:
Принадлежит:

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30-08-2010 дата публикации

СПОСОБ РЕГУЛИРОВАНИЯ ПОЛОЖЕНИЯ ОТСЕЧНОГО ЗОЛОТНИКА С ДИНАМИЧЕСКОЙ КОРРЕКЦИЕЙ ПОЛОЖЕНИЯ "НУЛЯ", ПРИМЕНЯЕМЫЙ В СИСТЕМЕ РЕГУЛИРОВАНИЯ ПАРОВОЙ ТУРБИНЫ

Номер: EA0201000166A1
Принадлежит:

Изобретение относится к области энергетики и может быть использовано в электрогидравлических системах регулирования паровых турбин с применением средств микропроцессорной техники. Предложен способ регулирования положения отсечного золотника, управляющего перемещением сервомотора, в свою очередь управляющего клапанами паровой турбины в системе регулирования паровой турбины, с динамической коррекцией смещения "нуля" отсечного золотника, включающий определение требуемой величины перемещения отсечного золотника для достижения заданного положения сервомотора и перемещение отсечного золотника в соответствии с ранее определенным значением, отличающийся тем, что на этапе определения величины перемещения отсечного золотника до начала регулирования измеряют значения смещения "нуля" отсечного золотника в различных положениях штока сервомотора во всем диапазоне перемещения этого штока; а при регулировании производят расчет величины динамической коррекции смещения нуля для заданного положения штока ...

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15-04-2005 дата публикации

СИСТЕМА АВТОМАТИЧНОГО РЕГУЛЮВАННЯ УПРАВЛІННЯ ПАРОВОЮ ТУРБІНОЮ

Номер: UA0000054347 C2

Спосіб автоматичного регулювання парової турбіни включає вплив тиском масла від насоса на регулятор швидкості і золотник керування сервоприводом регулюючих клапанів турбіни. Вплив тиском масла від насоса здійснюють безпосередньо на золотник керування спеціальним пневматичним клапаном - регулятором швидкості, що автоматично управляється сигналом з комп'ютера.

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30-08-2010 дата публикации

СПОСОБ РЕГУЛИРОВАНИЯ ПОЛОЖЕНИЯ ОТСЕЧНОГО ЗОЛОТНИКА С ДИНАМИЧЕСКОЙ КОРРЕКЦИЕЙ ПОЛОЖЕНИЯ "НУЛЯ", ПРИМЕНЯЕМЫЙ В СИСТЕМЕ РЕГУЛИРОВАНИЯ ПАРОВОЙ ТУРБИНЫ

Номер: EA0000013903B1

Изобретение относится к области энергетики и может быть использовано в электрогидравлических системах регулирования паровых турбин с применением средств микропроцессорной техники. Предложен способ регулирования положения отсечного золотника, управляющего перемещением сервомотора, в свою очередь управляющего клапанами паровой турбины в системе регулирования паровой турбины, с динамической коррекцией смещения ″нуля″ отсечного золотника, включающий определение требуемой величины перемещения отсечного золотника для достижения заданного положения сервомотора и перемещение отсечного золотника в соответствии с ранее определенным значением, отличающийся тем, что на этапе определения величины перемещения отсечного золотника до начала регулирования измеряют значения смещения ″нуля″ отсечного золотника в различных положениях штока сервомотора во всем диапазоне перемещения этого штока; а при регулировании производят расчет величины динамической коррекции смещения нуля для заданного положения штока ...

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11-12-2018 дата публикации

Improved turbine used for reducing hard particle damage and application method of improved turbine

Номер: CN0108979749A
Автор: SHI AOJIE
Принадлежит:

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06-06-2023 дата публикации

Energy recovery optimization method for large air separation steam-electric double-drive coaxial unit

Номер: CN116220838A
Принадлежит:

The invention provides an energy recovery optimization method for a large air separation steam-electricity double-drive coaxial unit. The method comprises the following steps that firstly, the large air separation steam-electricity double-drive coaxial unit with an independent lubricating oil and adjusting oil system is adopted; 2, automatic starting control of an oil pump is adjusted; step 3, controlling the operation of the large air separation steam-electric double-drive unit; fourthly, automatic stop control over the oil pump is adjusted; and 5, adjusting interlocking control of the oil pump. Aiming at industries such as nonferrous metallurgy, the steam turbine is adopted as a waste heat recovery system and drives the air compressor to operate together with the motor, waste heat energy is directly converted into mechanical energy from heat energy, the recovery efficiency is high, normal operation of a main process is not affected, meanwhile, the unit further has a power generation function ...

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22-04-1988 дата публикации

THERMOSENSITIVE OPERATING MACHINERY

Номер: FR0002508546B1
Принадлежит:

Подробнее
30-12-1914 дата публикации

Device of admission of vapor for steam turbines

Номер: FR0000473094A
Автор: MERTZ EMILE
Принадлежит:

Подробнее
02-02-2012 дата публикации

Systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel

Номер: US20120023894A1
Автор: Paul Joseph Martin
Принадлежит: General Electric Co

Certain embodiments of the invention may include systems, methods, and apparatus for monitoring corrosion or corrosive contaminants associated with liquid fuel. According to an example embodiment of the invention, a method is provided for monitoring and predicting corrosion. The method can include monitoring corrosion or corrosive contaminants associated with liquid fuel in a fuel supply system of a gas turbine, predicting, based at least in part on the monitoring, a cumulative level of corrosion of one or more components associated with a gas turbine, and outputting information associated with the monitoring.

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01-03-2012 дата публикации

Variable geometry turbine

Номер: US20120051882A1
Автор: John Frederick Parker
Принадлежит: Individual

A variable geometry turbine comprising a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.

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04-10-2012 дата публикации

Turbocharger assembly

Номер: US20120251352A1
Автор: Jeffrey Carter
Принадлежит: Cummins Turbo Technologies Ltd

According to an aspect of the present invention, there is provided a turbocharger assembly, comprising: a turbocharger; one or more actuators for controlling a flow of fluid in, around, or associated with the operation of the turbocharger; control electronics for use in controlling actuation of the one or more actuators; and boost electronics configured to receive an input voltage, and to provide a boosted output voltage to the control electronics.

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04-04-2013 дата публикации

Variable vane angular position sensor

Номер: US20130084179A1
Принадлежит: Hamilton Sundstrand Corp

A variable vane control system for use with a gas turbine engine includes an actuator, a mechanical linkage assembly, and a vane position sensor. The gas turbine engine has a plurality of variable vanes each having an airfoil disposed in a gas flow path of the gas turbine engine. The plurality of variable vanes includes a first variable vane. The mechanical linkage assembly operably connects the actuator to at least the first variable vane. The vane position sensor is connected to one of the first variable vane or a portion of the mechanical linkage assembly proximate the first variable vane for sensing angular position of the first variable vane.

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23-05-2013 дата публикации

DEVICE FOR CONTROLLING PIVOTABLE VANES OF A TURBO-MACHINE

Номер: US20130129487A1
Принадлежит: TURBOMECA

A control device for controlling pivotable vanes of a turbo-machine, including: a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; and a control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links; wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with other links being connected to the ring portion via respective sliding pivot connections. 16-. (canceled)7. A control device for controlling pivotable vanes of a turbo-machine , comprising:a plurality of pivotable vanes distributed in azimuth over at least 90° around the axis of the turbo-machine, the pivotable vanes being oriented substantially radially relative to the axis of the turbo-machine; anda control ring portion for controlling pivoting of the vanes, each vane being connected to the control ring portion by a link, the control ring portion being held around the axis of the turbo-machine by the links;wherein at least two of the links are connected to the ring portion by respective ball-joint connections, with each of other links being connected to the ring portion via respective sliding pivot connections.8. A control device according to claim 7 , wherein the two ball-joint connections are spaced apart in azimuth by about 90°.9. A control device according to claim 7 , wherein the two of the links connected to the ring portion via a respective ball-joint connection are rigid claim 7 , while the other links connected to the ring portion via respective sliding pivot connections are more flexible so as to be capable of deforming elastically.10. A control device according to claim 9 , wherein the more flexible links are elastically deformable in torsion ...

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30-05-2013 дата публикации

VARIABLE TURBINE GEOMETRY

Номер: US20130136581A1
Автор: Ammon Volkhard
Принадлежит: Bosch Mahle Turbo Systems GmbH & Co. KG

A variable turbine geometry may have guide blades rotatably mounted in a blade bearing ring. An adjusting ring may be arranged on the bearing ring and an actuator may be configured to adjust the adjusting ring via a link lever. An adjustable eccentric may be arranged on the link lever and guided in a groove arranged on the blade bearing ring. The eccentric may be configured to stop on at least one end of the groove to limit at least one minimal flow through the variable turbine geometry. 1. A variable turbine geometry , comprising: guide blades rotatably mounted in a blade bearing ring , an adjusting ring arranged on the bearing ring an actuator configured to adjust the adjusting ring via a link lever ,an adjustable eccentric arranged on the link lever and guided in a groove arranged on the blade bearing ring,wherein the eccentric is configured to stop on at least one end of the groove to limit at least one minimal flow through the variable turbine geometry.2. The variable turbine geometry according to claim 1 , wherein the eccentric is designed as an axial extension on a link lever head claim 1 , and wherein the link lever head is configured to interact with the adjusting ring.3. The variable turbine geometry according to claim 1 , wherein the groove on the blade bearing ring is open towards a face end and to the outside of the bearing ring.4. The variable turbine geometry according to claim 2 , wherein the eccentric is at least one of caulked claim 2 , riveted and spread to the link lever head.5. The variable turbine geometry according to claim 1 ,wherein the eccentric comprises includes a sleeve body, which can be inserted into an opening formed in the link lever head, and a holding portion of the sleeve body is arranged in the interior of the opening,wherein a core body is arranged in the interior of the sleeve body to radially brace the holding portion in the opening and fix the eccentric on the link lever head at least one of axially and rotationally.6. The ...

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11-07-2013 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20130177403A1
Принадлежит: Cummins Ltd.

A variable geometry turbine comprise a housing; a turbine wheel supported in the housing for rotation about a turbine axis: and an annular inlet passage upstream of said turbine wheel defined between respective inlet surfaces defined by an annular nozzle ring and a facing annular shroud. The nozzle ring and shroud are axially movable relative to one another to vary the size of the inlet passage; the nozzle ring having a circumferential array of inlet vanes extending across the inlet passage. The shroud covers the opening of a shroud cavity and defines a circumferential array of vane slots, each vane slot corresponding to an inlet vane, the vane slots and shroud cavity being configured to receive said inlet vanes to accommodate axial movement of the nozzle ring. At least one vane slot has a first side corresponding to a first side of the corresponding inlet vane and a second side corresponding to a second side of the corresponding inlet vane, the first side of the vane slot being located a shorter radial distance from the turbine wheel than the second side of the vane slot. The at least one vane slot has a leading end corresponding to a leading end of a corresponding inlet vane, and a trailing end downstream of the leading end, the trailing end corresponding to a trailing end of the inlet vane. A vane chord extends in a straight line between the a leading end tip and a trailing end tip of the inlet vane. The at least one vane slot has an increased clearance portion, the clearance between a portion of the at least one vane slot, which forms part of the increased clearance portion, and an adjacent portion of the inlet vane being greater than the clearance between a further portion of the at least one vane slot, which does not form part of the increased clearance portion, and an adjacent portion of the inlet vane. The increased clearance portion is located at the second side of the vane slot and extending from a trailing end tip of the trailing end of the vane slot to a ...

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19-09-2013 дата публикации

OPERATION CONTROL APPARATUS AND OPERATION CONTROL METHOD FOR STEAM TURBINE

Номер: US20130243574A1
Автор: Jahami Kazuhiro
Принадлежит:

A speed controller generates a speed control output signal based on an output target value and a detected speed of a steam turbine, an extraction pressure controller generates an extraction pressure control output signal based on an extraction flow rate target value and a detected extraction pressure of the steam turbine, and when operation signals of a governor valve and an extraction control valve are generated with reference to an extraction map for deriving opening degrees of the valves at an operation point determined depending on the signals, the extraction map is used with a scale of the extraction pressure control output signal in the extraction map being corrected to be multiplied by “extraction flow rate target value/extraction flow rate actual value” based on a regularly detected extraction flow rate actual value of the steam turbine. 1. An operation control apparatus for a steam turbine including at least a high-pressure turbine and a low-pressure turbine , the steam turbine further including a governor valve that controls a flow rate of steam to be supplied to the high-pressure turbine , and an extraction control valve that controls a flow rate of steam to be supplied from the high-pressure turbine to the low-pressure turbine , the operation control apparatus comprising:a speed controller that generates a speed control output signal based on an output target value of the steam turbine and a detected speed of the steam turbine;an extraction pressure controller that generates an extraction pressure control output signal based on an extraction flow rate target value of the steam turbine and a detected extraction pressure of the steam turbine; andan extraction map for deriving opening degrees of the governor valve and the extraction control valve at an operation point, the opening degrees being determined depending on the speed control output signal and the extraction pressure control output signal,wherein a scale of the extraction pressure control output ...

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26-12-2013 дата публикации

Four bar drive mechanism for bleed system

Номер: US20130341547A1
Принадлежит: Individual

An actuation system for a bleed valve includes first and second bell cranks connected by a connecting link. The first bell crank has a first arm that is coupled to a bleed valve and a second arm that is coupled to the connecting link. The connecting link has a first end coupled to the second arm of the first bell crank and a second end coupled to a first arm of the second bell crank. A second arm of the second bell crank is coupled to an actuating element. Input is communicated through the actuating element to move the bleed valve between open and closed positions via the first and second bell cranks.

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10-04-2014 дата публикации

TURBINE FOR AN EXHAUST GAS TURBOCHARGER

Номер: US20140099191A1
Автор: KOTZBACHER Thorben
Принадлежит: IHI Charging Systems International GmbH

In a turbine for exhaust gas turbocharger of a combustion engine with a turbine casing forming an installation space in which a turbine wheel is arranged so as to be rotatable about an axis of rotation and into which exhaust gas of the combustion engine may be supplied via at least one flow duct in which a guide vane structure is arranged, the guide vane structure includes vanes, which are pivotably supported relative to the turbine casing and form an axial inlet nozzle structure adjacent a wall portion of the turbine which extends along the guide vane structure, the wall portion comprising at least a first guide wall area which overlaps the guide vane structure, and which is set back relative to a second guide wall area in which the vanes are pivotably supported and which adjoins the first wall area. 1141820182238207238147218701272708072827080. A turbine for an exhaust gas turbocharger of a combustion engine , comprising a turbine casing () including an installation space () , a turbine wheel () arranged in the installation space () so as to be rotatable about an axis of rotation () at least one inlet flow duct () via which exhaust gas of the combustion engine may be supplied to the turbine wheel () , a guide vane structure () arranged in the inlet flow duct () and including vanes which are pivotably supported relative to the turbine casing () , the vane structure () being delimited in the axial direction of the installation space () at least partially by at least one wall portion () of the turbine () which is at least partially overlapping the guide vane structure () , the wall portion () comprising a first wall area () which is arranged adjacent the guide vane () , and which is set back relative to a second wall area () of the wall portion () adjoining the first wall area ().2708082725212. The turbine according to claim 1 , wherein the wall portion () with the first wall area () and the second wall area () is arranged at the side of the guide vane structure () ...

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07-01-2021 дата публикации

VANE ANGLE SYSTEM ACCURACY IMPROVEMENT

Номер: US20210003029A1
Автор: Ward Thomas W.
Принадлежит:

A stator vane angle system includes an engine case, a plurality of stator vanes located at an interior of the engine case. Each stator vane is rotatable about a stator vane axis. A synchronization ring is located at an exterior of the engine case. The synchronization ring is operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes. A plurality of impingement openings extend through the engine case from the interior of the engine case to the exterior of the engine case. The plurality of impingement openings are configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring, thereby reducing a thermal mismatch between the engine case and the synchronization ring. 1. A stator vane angle system , comprising:an engine case;a plurality of stator vanes disposed at an interior of the engine case, each stator vane rotatable about a stator vane axis;a synchronization ring disposed at an exterior of the engine case, the synchronization ring operably connected to each stator vane of the plurality of stator vanes such that movement of the synchronization ring urges rotation of each stator vane of the plurality of stator vanes about their respective stator vane axes; anda plurality of impingement openings extending through the engine case from the interior of the engine case to the exterior of the engine case, the plurality of impingement openings configured to direct flowpath gases from the interior of the engine case to impinge on the synchronization ring.2. The stator vane angle system of claim 1 , wherein the plurality of impingement openings each have an impingement opening outlet disposed at a same axial location as the synchronization ring.3. The stator vane angle system of claim 1 , wherein the plurality of impingement openings each extend perpendicular to ...

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14-01-2016 дата публикации

AERO-ACTUATED VANES

Номер: US20160010486A1
Автор: Christians Joseph T.
Принадлежит:

A turbomachinery vane includes a vane body defining a longitudinal axis, a trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis, and a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions. A gas turbine engine includes a turbomachinery component including a row of actuated stators, wherein the actuated stator row includes a plurality of the turbomachinery vanes. A method of actuating a vane by aerodynamic loads includes moving the vane about a pivot point from a first position to a second position by a first set of by aerodynamic loads. 1. A turbomachinery vane comprising:a vane body defining a longitudinal axis; anda trunnion extending from the vane body and defining a pivot point for pivoting the vane body about the longitudinal axis.2. A vane as recited in claim 1 , further comprising a lock system operatively connected to the trunnion and configured to lock the vane body in a plurality of locked positions.3. A vane as recited in claim 2 , wherein the vane body includes a leading edge claim 2 , an opposed trailing edge claim 2 , a high pressure side claim 2 , and an opposed low pressure side claim 2 , and the trunnion is located at a position relative to the leading edge claim 2 , the trailing edge claim 2 , the high pressure side claim 2 , and the low pressure side for aerodynamic loads to pivot the vane body.4. A vane as recited in claim 3 , wherein the trunnion is located at a position relative to the leading edge claim 3 , the trailing edge claim 3 , the high pressure side claim 3 , and the low pressure side for a first set of aerodynamic loads pivot the vane body from a first locked position to the second locked position and a second set of aerodynamic loads pivot the vane body from the second locked position to a first locked position.5. A vane as recited in claim 1 , wherein the lock system is configured to release the ...

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14-01-2016 дата публикации

VANE ASSEMBLY FOR AN UNDUCTED THRUST PRODUCING SYSTEM

Номер: US20160010487A1
Принадлежит: GENERAL ELECTRIC COMPANY

A unshrouded vane assembly for an unducted propulsion system includes a plurality of vanes which have non-uniform characteristics configured to generate a desired vane exit swirl angle. 1. A unshrouded vane assembly for an unducted propulsion system , comprising a vane assembly having a plurality of vanes which have non-uniform characteristics with respect to one another configured to generate a desired vane exit swirl angle.2. The vane assembly of claim 1 , wherein said vanes have a non-uniform characteristic selected from the group consisting of: camber claim 1 , stagger claim 1 , circumferential spacing claim 1 , axial position claim 1 , span claim 1 , tip radius claim 1 , and combinations thereof.3. The vane assembly of claim 2 , wherein said vanes have a root claim 2 , a tip claim 2 , and a span therebetween claim 2 , and wherein said non-uniform characteristic is attributed to a portion of the span of said vanes.4. The vane assembly of claim 3 , wherein said non-uniform characteristic is attributed to substantially all of the span of said vanes.5. The vane assembly of claim 1 , wherein said vanes are variable in pitch.6. The vane assembly of claim 5 , wherein said vanes are individually variable in pitch.7. The vane assembly of claim 5 , wherein a plurality of said vanes are variable in pitch in conjunction with one another.8. An unducted propulsion system claim 5 , said propulsion system comprising a rotating element having an axis of rotation and a stationary element claim 5 , said rotating element having a plurality of blades each having a blade root proximal to said axis claim 5 , a blade tip remote from said axis claim 5 , and a blade span measured between said blade root and said blade tip claim 5 , wherein said stationary element has a plurality of vanes each having a vane root proximal to said axis claim 5 , a vane tip remote from said axis claim 5 , and a vane span measured between said vane root and said vane tip configured to impart a change in ...

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17-04-2014 дата публикации

METHOD AND A SYSTEM FOR ADJUSTING NOZZLE AREA IN STEAM TURBINES

Номер: US20140105720A1
Принадлежит:

The various embodiments herein provide a method and a system for controlling a nozzle area in a steam turbine. The system comprises a nozzle ring provided with a plurality of nozzle blades at an outer edge. The steam enters into the nozzle ring and jets out on the blades of the rotor disk. When there is an off design condition, the nozzle blades are plugged or opened by adding or removing the inserts. The nozzle area is increased or decreased by opening or plugging the nozzle passages manually or automatically with the help of the inserts. The embodiments herein provide a cost effective and simple solution to deal with the off design conditions. 1. A system for adjusting a nozzle area in a steam turbine comprising:a nozzle ring;a plurality of nozzle blades provided in the nozzle ring; andan insert to block a nozzle passage formed between two adjacent nozzle blades in the plurality of nozzle blades;wherein the insert block the nozzle passages to control a flow of a driving fluid during an off-design condition.2. The system according to claim 1 , wherein the nozzle passages are plugged by the inserts manually to decrease a nozzle area claim 1 , and wherein the nozzle passages are plugged by the inserts manually to decrease a nozzle area in a full admission turbine or in a partial admission turbine.3. The system according to claim 1 , wherein the inserts are removed from the nozzle passages manually to increase a nozzle area claim 1 , and wherein the inserts are removed from the nozzle passages manually to increase a nozzle area in a full admission turbine or in a partial admission turbine.4. The system according to claim 1 , wherein a number of nozzle passages are blocked by inserting the inserts based on a demand of the driving fluid in an off-design condition claim 1 , and wherein a reduction or a variation in a demand of a driving fluid is caused in the off-design condition.5. The system according to claim 1 , wherein the inserts are provided with a socket head ...

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05-02-2015 дата публикации

SYSTEM AND METHOD FOR A GAS TURBINE ENGINE SENSOR

Номер: US20150033757A1
Принадлежит:

A system includes a gas turbine engine that includes a combustor section having a turbine combustor that generates combustion products, a turbine section having one or more turbine stages driven by the combustion products, an exhaust section disposed downstream of the turbine section, an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof, and an oxygen sensor disposed in the oxygen sensor adaptor housing. The oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold. 1. A system , comprising: a combustor section having a turbine combustor that generates combustion products;', 'a turbine section having one or more turbine stages driven by the combustion products;', 'an exhaust section disposed downstream of the turbine section;', 'an oxygen sensor adaptor housing disposed in at least one of the combustor section, the turbine section, or the exhaust section, or any combination thereof; and', 'an oxygen sensor disposed in the oxygen sensor adaptor housing, wherein the oxygen sensor adaptor housing is configured to maintain a temperature of a portion of the oxygen sensor below an upper threshold., 'a gas turbine engine, comprising2. The system of claim 1 , wherein the oxygen sensor comprises at least one of a wideband oxygen sensor claim 1 , a lambda sensor claim 1 , an air/fuel meter claim 1 , or a universal exhaust gas oxygen (UEGO) sensor claim 1 , or any combination thereof.3. The system of claim 1 , wherein the portion of the oxygen sensor comprises at least one of a hex section claim 1 , a gland packing claim 1 , wiring claim 1 , or a connector shell claim 1 , or any combination thereof.4. The system of claim 1 , wherein the oxygen sensor comprises a heater configured to maintain a tip temperature of a tip portion of the oxygen sensor within a temperature range.5. The system of claim 1 , ...

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11-02-2016 дата публикации

Variable Area Nozzle and Associated Propulsion System and Method

Номер: US20160040625A1
Принадлежит:

A nozzle including a frame having a plurality of deflecting elements arranged in an array, the array extending about a longitudinal axis, and a skin positioned over the frame. 1. A nozzle comprising:a frame comprising a plurality of deflecting elements arranged in an array, said array extending about a longitudinal axis; anda skin positioned over said frame.2. The nozzle of wherein each deflecting element of said plurality of deflecting elements is connected at a vertex to adjacent deflecting elements of said plurality of deflecting elements.3. The nozzle of wherein each deflecting element of said plurality of deflecting elements produces a lateral displacement in response to a deflection force applied in a direction substantially parallel to said longitudinal axis.4. The nozzle of wherein each deflecting element of said plurality of deflecting elements comprises a rectilinear frame structure.5. The nozzle of wherein each deflecting element of said plurality of deflecting elements comprises a square frame structure.6. The nozzle of wherein each deflecting element of said plurality of deflecting elements comprises a curvilinear frame structure.7. The nozzle of wherein each deflecting element of said plurality of deflecting elements comprises a continuous frame structure.8. The nozzle of wherein at least one deflecting element of said plurality of deflecting elements comprises a hinge.9. The nozzle of wherein at least one deflecting element of said plurality of deflecting elements comprises a biasing element.10. The nozzle of wherein said skin comprises a stretchable material.11. The nozzle of wherein said skin comprises a plurality of plates claim 1 , strips or tiles.12. The nozzle of further comprising an actuation assembly operatively connected to said frame to supply a deflection force to said frame.13. The nozzle of wherein said actuation assembly supplies said deflection force in a direction substantially parallel with said longitudinal axis.14. The nozzle of ...

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26-02-2015 дата публикации

Detection system for identifying blockages in guide vanes of a turbine engine

Номер: US20150056077A1
Автор: Nikolai R. Tevs
Принадлежит: Siemens Energy Inc

A detection system for a turbine engine that is configured to identify the presence of at least a partial blockage of guide vanes by monitoring deflection of an adjacent row of turbine blades. The detection system may include one or more sensors positioned radially outward from tips of turbine blades in a row of turbine blades adjacent an upstream row of guide vanes that remain stationary. The detection system may also include a conditioning module in communication with the sensor to amplify the output signals received from the sensor. A processing module may be in communication with conditioning module to analyze signals produced by the sensor via the conditioning module and generate an alarm if the processing module detects a change in amplitude, such as an increase of amplitude at frequencies between about 400 Hertz and about 900 Hertz.

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23-02-2017 дата публикации

ACTUATOR CONTROL

Номер: US20170051629A1
Автор: SUTHERLAND Roger A
Принадлежит: ROLLS-ROYCE PLC

An actuation system comprises a fluid supply that is fluidly connected to a position control actuator The output of the position control actuator is determined by the fluid supply. The fluid supply is controlled by a piezoelectric actuator 1. An actuation system comprising:a fluid supply conduit;a piezoelectric actuator; anda position control actuator, wherein:the fluid supply conduit is in fluid communication with the position control actuator, such that the position control actuator can be controlled by the supply of fluid thereto; andthe piezoelectric actuator is positioned in the fluid supply conduit, such that the flow in the fluid supply conduit can be regulated by the piezoelectric actuator.2. An actuation system according to claim 1 , further comprising an actuator position control system arranged to control the excitation of the piezoelectric actuator based on the position of the position control actuator.3. An actuation system according to claim 2 , wherein the actuator position control system comprises:a position sensor arranged to sense the position of the position control actuator; anda control unit arranged to receive a signal representative of the sensed position from the position sensor, and to send an excitation signal to the piezoelectric actuator based at least in part on the sensed position of the position control actuator.4. An actuation system according to claim 1 , wherein:the piezoelectric actuator is transformable between a first configuration and second configuration; andwhen the piezoelectric actuator is in the first configuration, fluid in the fluid supply conduit can pass from an upstream side of the piezoelectric actuator to a downstream side of the piezoelectric actuator, whereas in the second configuration fluid is blocked from passing from the upstream to the downstream side of the piezoelectric actuator.5. An actuation system according to claim 4 , wherein in the second configuration the fluid conduit is open at the piezoelectric ...

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15-05-2014 дата публикации

Turbocharger and Variable-Nozzle Cartridge Therefor

Номер: US20140134015A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A variable-vane assembly for a turbocharger includes an annular nozzle ring supporting an array of rotatable vanes, an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending radially out from one end of the tubular portion and being axially spaced from the nozzle ring with the vanes therebetween, and an annular retainer ring disposed radially outward of the nozzle ring and extending generally radially inwardly. The nozzle ring's face is stepped, and a radially inner edge of the retainer ring engages the face of the nozzle ring radially outward of the step, the radially inner edge of the retainer ring having an axial thickness that is less than the step height such that a remaining portion of the step is presented to the exhaust gas flowing through the nozzle. 1. A turbocharger having a variable-nozzle turbine , comprising:a turbine assembly comprising a turbine housing and a turbine wheel mounted in the turbine housing and connected to a rotatable shaft for rotation therewith, the turbine housing defining a chamber surrounding the turbine wheel for receiving exhaust gas from an engine and for supplying the exhaust gas to the turbine wheel, the turbine assembly defining a nozzle leading from the chamber generally radially inwardly to the turbine wheel, the turbine housing further defining an axially extending bore through which exhaust gas is discharged after passing through the turbine wheel;a compressor assembly comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the rotatable shaft for rotation therewith;a center housing connected between the compressor housing and the turbine housing; and a generally annular nozzle ring having opposite first and second faces, the first face forming one wall of the nozzle, and an insert having a tubular portion sealingly received into the bore of the turbine housing and having a nozzle portion extending ...

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03-03-2016 дата публикации

CONTROL SYSTEM FOR A HEAT ENGINE SYSTEM UTILIZING SUPERCRITICAL WORKING FLUID

Номер: US20160061055A1
Автор: Bowan Brett A.
Принадлежит: ECHOGEN POWER SYSTEMS, L.L.C.

A heat engine system and a method for generating electrical energy from the heat engine system are provided. The method includes circulating via a turbo pump a working fluid within a working fluid circuit of the heat engine system. The method also includes transferring thermal energy from a heat source stream to the working fluid by at least a primary heat exchanger, feeding the working fluid into a power turbine and converting the thermal energy from the working fluid to mechanical energy, and converting the mechanical energy into electrical energy by a generator coupled to the power turbine. At least one valve operatively coupled to a control system is modulated in order to synchronize the generator with an electrical grid. A generator breaker is closed such that the generator and electrical grid are electrically coupled and the electrical energy is supplied to the electrical grid. 1. A method for synchronizing a generator of a heat engine system with an electrical grid , comprising:circulating, via a turbo pump, a working fluid within a working fluid circuit of the heat engine system, wherein the working fluid circuit has a high pressure side and a low pressure side and at least a portion of the working fluid is in a supercritical state;transferring thermal energy from a heat source stream to the working fluid by at least a primary heat exchanger fluidly coupled to and in thermal communication with the high pressure side of the working fluid circuit;feeding the working fluid into a power turbine and converting the thermal energy from the working fluid to mechanical energy of the power turbine;converting the mechanical energy into electrical energy by the generator coupled to the power turbine;comparing at least one electrical energy parameter of the electrical energy converted by the generator with at least one grid parameter of the electrical grid configured to be electrically coupled to the generator; andmodulating at least one valve of a plurality of valves ...

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01-03-2018 дата публикации

Valve Stroke And Spindle Way Counter Module For A Valve And Actuator Monitoring System

Номер: US20180058249A1
Автор: REIGL Martin
Принадлежит:

The present application provides a method of evaluating spindle component wear in a turbine by a data acquisition system. The method may include the steps of receiving a number of operating parameters from a number of sensors, wherein the operating parameters may include spindle position from which a number of spindle strokes and an accumulated spindle distance may be determined and temperature, generating a movement history based on the operating parameters, comparing the movement history to predetermined values, and altering one or more of the operating parameters and/or initiating repair procedures if the movement history exceeds predetermined values. 1. A method of evaluating spindle component wear in a turbine by a data acquisition system , comprising:receiving a plurality of operating parameters from a plurality of sensors;wherein the plurality of operating parameters comprises spindle position from which a number of spindle strokes and an accumulated spindle distance may be determined and temperature;generating a movement history based on the plurality of operating parameters;comparing the movement history to predetermined values; andaltering one or more of the plurality of operating parameters and/or initiating repair procedures if the movement history exceeds predetermined values.2. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises repairing and/or replacing a spindle claim 1 , a spindle guide claim 1 , a spindle seal claim 1 , and/or a spindle packing.3. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises taking a valve out of service.4. The method of claim 1 , wherein the step of altering one or more of the plurality of operating parameters and/or initiating repair procedures comprises ordering parts.5. The method of claim 1 , wherein the step of generating ...

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20-02-2020 дата публикации

STEAM TURBINE AND STEAM TURBINE CONTROL METHOD

Номер: US20200056500A1
Принадлежит:

A steam turbine () includes an inner casing () which has an inner casing body () in which a first main flow path () to which steam is supplied from an inner introduction port () is formed, an outer casing () which has an outer casing body () which forms a second main flow path () between the inner casing body () and the outer casing body () and an upper discharge port () and a lower discharge port () which are provided in the outer casing body () and through which exhaust steam (S) is discharged, an upper valve () and a lower valve () which adjust a flow rate of the discharged exhaust steam (S), and a control unit () which can independently control the upper valve () and the lower valve (). 112-. (canceled)13. A steam turbine comprising:an inner casing which has an inner casing body which covers a rotor that is configured to rotate around an axis extending in a horizontal direction from an outside in a radial direction about the axis and in which a first main flow path through which steam flows is formed between an outer peripheral surface of the rotor and the inner casing body and an inner introduction port through which the steam is supplied to the first main flow path;an outer casing which has an outer casing body which covers the inner casing from the outside in the radial direction and forms a second main flow path which communicates with the first main flow path and through which exhaust steam flows between an outer peripheral surface of the inner casing body and the outer casing body, an outer introduction port through which the steam is introduced into the inner introduction port, an upper discharge port which is provided in an upper portion of the outer casing body and through which the exhaust steam is discharged from the second main flow path, and a lower discharge port which is provided in a lower portion of the outer casing body and through which the exhaust steam is discharged from the second main flow path;an upper valve which adjusts a flow rate of ...

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29-05-2014 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20140147255A1
Принадлежит: Cummins Turbo Technologies Limited

A variable geometry turbine comprises: a turbine wheel in a housing assembly defining a radial gas flow inlet passage; an annular wall member which is displaceable to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member operably connected to the annular wall member to control displacement of the wall member. The actuating member has a terminal portion defining a radially extending flange and extends in a direction substantially parallel to the turbine axis through an aperture defined by a retaining member to locate the radially extending flange in between said retaining member and annular wall member. The terminal portion is contacted by the retaining member to connect the actuating member to the annular wall member. The aperture defines a clearance to accommodate displacement of the retaining member relative to the actuating member. 1. A variable geometry turbine comprising:a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis, said housing assembly defining a radial gas flow inlet passage upstream of said turbine wheel;an annular wall member defining one wall of said inlet passage and which is displaceable in a direction substantially parallel to said turbine axis to control gas flow through the inlet passage; anda linkage mechanism comprising at least one actuating member operably connected to said annular wall member to control displacement of said wall member,wherein said actuating member has a terminal portion that defines a radially extending flange, and said actuating member extends in a direction substantially parallel to said turbine axis through an aperture defined by a retaining member such that said radially extending flange is located in between said retaining member and said annular wall member,said terminal portion of the actuating member defining a first bearing surface extending transverse to said turbine axis, said first bearing surface being ...

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11-03-2021 дата публикации

PITCH CONTROL ASSEMBLY FOR AN AIRCRAFT-BLADED ROTOR

Номер: US20210071539A1
Автор: Tomescu Dana
Принадлежит:

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface and are circumferentially spaced around the circular disk. The position markers have a top surface elevated with respect to the root surface and opposing first and second side surfaces. The side surfaces of the position markers have a curved concave profile extending toward the root surface. 1. A feedback device for use in a gas turbine engine , the feedback device comprising:a circular disk coupled to rotate with a rotor of the gas turbine engine and to move along a longitudinal axis of the rotor, the circular disk having first and second opposing faces and defining a root surface that extends between and circumscribes the first and second faces; anda plurality of position markers extending radially from the root surface and circumferentially spaced around the circular disk, the position markers having a top surface elevated with respect to the root surface and opposing first and second side surfaces, the side surfaces of the position markers having a curved concave profile extending toward the root surface.2. The feedback device of claim 1 , wherein the top surface of the position marker and a portion extending toward the root surface by a predetermined distance is composed of a material having a higher magnetic permeability than that of the circular disk.3. The feedback device of claim 2 , wherein a majority of the position marker is composed of the material.4. The feedback device of claim 2 , wherein the ...

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23-03-2017 дата публикации

GEOMETRY FOR INCREASING TORQUE CAPACITY OF RIVETED VANE LEVER

Номер: US20170081975A1
Принадлежит:

A number of variations may include a product comprising: a vane lever comprising a first end; a second end; a top surface; and a bottom surface; and an opening defined by an inner surface which extends through the top surface and the bottom surface of the second end, and wherein at least a portion of the inner surface comprises a non-cylindrical, multi-lobed shape. 1. A product comprising: a vane lever comprising a first end; a second end; a top surface; and a bottom surface; and an opening which extends through the top surface and the bottom surface of the second end , wherein the opening is defined by an inner surface and at least one intervening surface between the inner surface and the top surface , wherein at least a portion of the opening comprises a non-cylindrical , multi-lobed shape; and wherein the intervening surface extends between the top surface and the inner wall at each of the lobes only.2. (canceled)3. (canceled)4. The product of wherein the intervening surface is at least one of rounded claim 1 , chamfered claim 1 , grooved claim 1 , or a plurality of ridges.5. The product of further comprising a vane component claim 1 , wherein the vane component comprises a vane rotatably mounted to a vane shaft claim 1 , wherein the vane shaft includes a stepped portion; and wherein the stepped portion extends through the non-cylindrical claim 1 , multi-lobed opening of the vane lever and is attached to the vane lever.6. The product of wherein the stepped portion is cylindrical.7. The product of wherein the stepped portion is non-cylindrical.8. The product of wherein the vane shaft is riveted to the vane lever.9. A vane pack assembly comprising:an upper vane ring;a lower vane ring;a plurality of vane components each having a vane shaft and a vane interposed between the upper vane ring and the lower vane ring;an adjustment ring surrounding a portion of the upper vane ring having a plurality of openings; anda plurality of vane levers each having a non-cylindrical, ...

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12-03-2020 дата публикации

SYSTEM FOR ADJUSTING A VARIABLE POSITION VANE IN AN AIRCRAFT ENGINE

Номер: US20200080441A1
Автор: FARRELL Ian
Принадлежит:

A system for adjusting a variable position vane in an aircraft engine is disclosed. The system comprises a servo valve operatively connected to the variable position vane and configured to cause adjustment of the variable position vane based on a pressure of air pressurized by a compressor of the aircraft engine. 1. A system for adjusting a variable position vane in an aircraft engine , the system comprising:a fluid-actuated actuator operatively connected to cause positional adjustment of the variable position vane;a servo valve including a valve member cooperating with a spool to control a flow of fluid to the fluid-actuated actuator, the servo valve configured to control the flow of fluid to the fluid-actuated actuator based on an input indicative of a pressure of air pressurized by a compressor of the aircraft engine and positional feedback from the variable position vane; anda transducer configured to generate the input to the servo valve based on a received signal indicative of the pressure of the air pressurized by the compressor of the aircraft engine.2. The system as defined in claim 1 , wherein the valve member and the spool are separately rotatable about a common axis.3. The system as defined in claim 1 , wherein the input includes a positional setting of the valve member.4. The system as defined in claim 3 , wherein the positional feedback from the variable position vane includes a positional setting of the spool.5. The system as defined in claim 1 , wherein the transducer converts a pressure differential to a linear position.6. The system as defined in claim 5 , wherein:the transducer includes a bellows;an interior of the bellows is exposed to the pressure of the air pressurized by the compressor; andan exterior of the bellows is exposed to an ambient pressure.7. The system as defined in claim 6 , including a movable member having a position indicative of the linear position provided by the transducer claim 6 , the movable member being urged in a first ...

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19-06-2014 дата публикации

STOPPER STRUCTURE FOR REGULATING OPENING DEGREE OF NOZZLE VANE IN TURBOCHARGER

Номер: US20140169949A1
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A stopper is provided with: a nut-receiving part provided on a heat insulation plate that is attached to an actuator bracket ; and a movable-side stopper part provided on an actuator rod that moves in relation to the heat insulation plate . An actuator is provided with an actuator body that generates driving force, and the actuator rod which transmits the driving force from the actuator body . The movable-side stopper part is provided on the actuator rod that extends from the actuator body to the nozzle vane side. 15-. (canceled)6. An opening degree regulating structure for a nozzle vane in a turbocharger , the structure comprising:a variable nozzle mechanism which is configured to change an opening degree of the nozzle vane by an actuator attached to a turbocharger body so as to change a flow rate of exhaust gas flowing to a turbine wheel; anda stopper which is configured to regulate an opening degree of the nozzle vane on a full-open side or a full-close side and also adjust the opening degree of the nozzle vane on the full-open side or the full-close side,wherein an actuator-side assembly of the variable nozzle mechanism is externally arranged and comprises a support shaft which is connected to a nozzle vane side and is supported rotatably by a bearing housing, an outer lever connected to the support shaft at one end to change the opening degree of the nozzle vane, a connection mechanism connected to the other end of the outer lever via a connection pin and configured to be adjustable in length, and an actuator having an actuator rod connected to the connection mechanism, andwherein the stopper is constituted by a first stopper part formed in a plane perpendicular to the actuator rod, and a second stopper part provided in a movable part which moves in a direction (L) of moving away from the first stopper part and being contactable with the first stopper part, the second stopper part being disposed on a body connected to the outer lever or on the actuator rod.7. ...

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19-03-2020 дата публикации

INTEGRAL HALF VANE, RINGCASE, AND ID SHROUD

Номер: US20200088046A1
Принадлежит:

A vane stage includes a ringcase extending circumferentially about a center axis of the vane stage. The ringcase extends completely about the center axis to form a first ring. An inner shroud extends circumferentially about the center axis of the vane stage. The inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis. A plurality of stationary half vanes extend radially between the ringcase and the inner shroud, and are circumferentially spaced about the center axis. The plurality of stationary half vanes are integral with the ringcase and the inner shroud. 1. A vane stage comprising:a ringcase extending circumferentially about a center axis of the vane stage, wherein the ringcase extends completely about the center axis to form a first ring;an inner shroud extending circumferentially about the center axis of the vane stage, wherein the inner shroud extends completely about the center axis to form a second ring positioned radially within the ringcase relative the center axis; anda plurality of stationary half vanes extending radially between the ringcase and the inner shroud, wherein the plurality of stationary half vanes are circumferentially spaced about the center axis, andwherein the plurality of stationary half vanes are integral with the ringcase and the inner shroud.2. The vane stage of claim 1 , wherein each of the plurality of stationary half vanes comprises:a leading edge extending radially from the inner shroud to the ringcase;a concave groove extending radially from the inner shroud to the ringcase and aft of the leading edge;a partial suction surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the concave groove; anda partial pressure surface extending radially from the inner shroud to the ringcase and extending axially from the leading edge to the concave groove opposite the partial suction surface, andwherein ...

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14-04-2016 дата публикации

Gas Turbine Engine Convergent/Divergent Nozzle With Unitary Synchronization Ring For Roller Track Nozzle

Номер: US20160102574A1
Автор: Peters Donald W
Принадлежит:

A nozzle system includes a static structure including a multiple of convergent flap rails and a synchronization ring including an inner ring radially spaced from an outer ring via a multiple of struts. The multiple of convergent flap rails extend at least partially between the inner ring and the outer ring. 1. A nozzle system comprising:a static structure including a multiple of convergent flap rails; anda synchronization ring adjacent to said static structure, said synchronization ring of a unitary structure including an inner ring radially spaced from an outer ring via a multiple of struts, said multiple of convergent flap rails extend at least partially between said inner ring and said outer ring.2. The nozzle system as recited in claim 1 , wherein said multiple of convergent flap rails are circumferentially spaced about an engine axis claim 1 , said multiple of struts arranged in pairs such that each strut is defined along an axis that intersects with said engine axis.3. The nozzle system as recited in claim 1 , wherein each of said multiple of convergent flap rails includes a first radial wall claim 1 , a second radial wall claim 1 , and an outer wall therebetween.4. The nozzle system as recited in claim 3 , wherein an aft section of each of said multiple of convergent flap rails curves toward an engine axis.5. The nozzle system as recited in claim 4 , wherein said aft section includes a track to at least partially support each of a multiple of convergent flaps.6. The nozzle system as recited in claim 5 , wherein each of said multiple of convergent flaps are pivotally coupled to said inner ring at an inner hinge interface.7. The nozzle system as recited in claim 6 , further comprising a multiple of divergent flaps claim 6 , each of said multiple of divergent flaps are respectively pivotally coupled to one of said multiple of convergent flaps.8. The nozzle system as recited in claim 7 , further comprising a multiple of links claim 7 , each of said multiple of ...

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26-03-2020 дата публикации

VARIABLE VANE MECHANISM OF TURBOCHARGER HAVING PREDETERMINED VANE CLEARANCE

Номер: US20200095886A1
Принадлежит: Garrett Transportation I Inc.

A method of manufacturing a variable vane mechanism includes arranging a vane and a spacer between a first support structure and a tool member of a tool. The method also includes abutting a first inner surface of the first support structure against a first side surface of the vane and a second side surface of the vane against an opposing surface of the tool member, leaving a control surface of the spacer projecting from the first support structure at a predetermined distance. The method further includes fixedly attaching the spacer to the first support structure with the control surface of the spacer projecting from the first support structure at the predetermined distance. The method further includes abutting a second support structure on the control surface of the spacer to define a gap between the first support structure and the second support structure with the vane disposed within the gap. 1. A method of manufacturing a variable vane mechanism comprising:arranging a vane and a spacer between a first support structure and a tool member of a tool;abutting a first inner surface of the first support structure against a first side surface of the vane and a second side surface of the vane against an opposing surface of the tool member, leaving a control surface of the spacer projecting from the first support structure at a predetermined distance;fixedly attaching, while abutting the first inner surface against the first side surface and the second side surface against the opposing surface, the spacer to the first support structure with the control surface of the spacer projecting from the first support structure at the predetermined distance; andabutting, after fixedly attaching the spacer to the first support structure, a second support structure on the control surface of the spacer to define a gap between the first support structure and the second support structure, the vane disposed within the gap.2. The method of claim 1 , further comprising providing the tool ...

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23-04-2015 дата публикации

RANKINE CYCLE APPARATUS

Номер: US20150107252A1
Принадлежит:

A Rankine cycle apparatus (A) of the present disclosure includes a main circuit (), a heat exchange portion (HX), a bypass flow path (), a flow rate-adjusting mechanism (), and a pair of temperature sensors (A). The main circuit () is formed by an expander (), a condenser (), a pump (), and an evaporator () that are circularly connected in this order. The heat exchange portion (HX) is located in the main circuit () at a position between an outlet of the expander () and an inlet of the pump (). The bypass flow path () branches from the main circuit () at a position between an outlet of the evaporator () and an inlet of the expander (), and joins to the main circuit () at a position between the outlet of the expander () and an inlet of the heat exchange portion (HX). The flow rate-adjusting mechanism () adjusts the flow rate of the working fluid in the bypass flow path (). The pair of temperature sensors (A) detects temperatures of the working fluid at two positions spaced from each other in a flow direction of the working fluid. 1. A Rankine cycle apparatus comprising:a main circuit formed by an expander, a condenser, a pump, and an evaporator that are circularly connected in this order;a heat exchange portion located in the main circuit at a position between an outlet of the expander and an inlet of the pump;a bypass flow path branching from the main circuit at a position between an outlet of the evaporator and an inlet of the expander and joining to the main circuit at a position between the outlet of the expander and an inlet of the heat exchange portion;a flow rate-adjusting mechanism that adjusts a flow rate of a working fluid in the bypass flow path; anda pair of temperature sensors that detects temperatures of the working fluid at two positions spaced from each other in a flow direction of the working fluid in a portion of the main circuit between a junction point at which the bypass flow path joins to the main circuit and an inlet of the evaporator, wherein ...

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13-04-2017 дата публикации

FLUID MACHINE WITH VARIABLE VANES

Номер: US20170101885A1
Автор: Lemke Paul, Wygant Karl
Принадлежит: HANWHA TECHWIN CO., LTD.

A fluid machine with variable vanes includes: a case, a plurality of vanes arranged along a circumferential direction of the case; a transmission ring rotatably provided in the case and configured to rotate with respect to the case; a transmission member provided on the transmission ring; and a driving assembly detachably attached to the case and including: a driving shaft; and a connection member connected to the transmission member through a through hole of the case provided at a position corresponding to the transmission member and configured to rotate together with the driving shaft, wherein the connection member is disengageably engaged with the transmission member such that the driving assembly is disconnected from the case through the through hole. 1. A fluid machine with variable vanes , the fluid machine comprising:a case comprising a passage through which a fluid passes;a plurality of vanes arranged along a circumferential direction of the passage of the case and configured to rotate to control an amount of the fluid passing through the passage;a transmission ring rotatably provided in the case and configured to rotate with respect to the case, the plurality of vanes being attached to the transmission ring to rotate with the transmission ring;a transmission member provided on the transmission ring and configured to transmit an external rotation force to the transmission ring; and a driving shaft provided at an exterior of the case to rotate with respect to a first axis extending in a direction crossing a rotation axis of the transmission ring; and', 'a connection member provided at a first end of the driving shaft, connected to the transmission member through a through hole of the case provided at a position corresponding to the transmission member and configured to rotate together with the driving shaft,, 'a driving assembly detachably attached to the case and comprisingwherein the connection member is disengageably engaged with the transmission member ...

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30-04-2015 дата публикации

EXHAUST-GAS TURBOCHARGER

Номер: US20150118029A1
Принадлежит:

An exhaust-gas turbocharger which has a radial bearing with a simple design which can quickly and easily be mounted. A pin/rolling roller arrangement is provided as the radial bearing. The pin is in this case fixed on the vane bearing ring. The rolling roller is placed onto the pin and, in the mounted state, an inner wall region of the unison ring is supported on the rolling roller mounted rotatably on the pin. 11. An exhaust-gas turbocharger () having{'b': '2', 'claim-text': {'b': 3', '4, 'which has a turbine wheel () surrounded by an intake duct (), and'}, 'a turbine (),'}{'b': '5', 'claim-text': [{'b': 6', '7', '4, 'a washer () and a vane bearing ring (), which delimit the intake duct (),'}, {'b': 8', '4', '7', '9', '10', '11', '12', '13', '7, 'a plurality of vanes (), which are arranged in the intake duct () and are mounted in the vane bearing ring () by way of rotatable vane shafts (), which are connected to vane levers (), the lever heads () of which engage into associated grooves () in a unison ring (), which surrounds the vane bearing ring () on the outside, and'}, {'b': 7', '13, 'a radial bearing between the vane bearing ring () and the unison ring (),'}], 'a VTG cartridge (), with'}wherein{'b': 14', '7', '15', '16', '13, 'the radial bearing has at least one pin (), which is fixed on the vane bearing ring () and onto which a rolling roller () is placed, against which an inner wall region () of the unison ring () bears.'}2147. The exhaust-gas turbocharger as claimed in claim 1 , wherein the pin () is butt-welded onto the vane bearing ring ().3182014. The exhaust-gas turbocharger as claimed in claim 1 , wherein a lock washer () is fastened on the free end () of the pin ().41820. The exhaust-gas turbocharger as claimed in claim 3 , wherein the lock washer () is fastened on the free end () at a defined distance (A) from the upper side (OS) of the rolling roller.5182019. The exhaust-gas turbocharger as claimed in claim 3 , wherein the lock washer () is fastened ...

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09-06-2022 дата публикации

VARIABLE STATOR VANES WITH ANTI-LOCK TRUNNIONS

Номер: US20220178270A1
Принадлежит:

Variable stator vanes with anti-lock trunnions are disclosed. An example apparatus disclosed herein includes an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis, an outer trunnion, and an inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine. 1. An apparatus comprising:an airfoil to be disposed within a flow path of a gas turbine engine, the gas turbine engine defining an axial axis, a radial axis and a circumferential axis;an outer trunnion; andan inner trunnion including a curved surface in an axial-radial plane, the inner trunnion enabling the airfoil to be rotatably mounted to an inner shroud of the gas turbine engine via an opening of a trunnion ring, the trunnion ring including a first component and a second component coupled together via a fastener to form the opening.2. The apparatus of claim 1 , wherein the airfoil claim 1 , the outer trunnion claim 1 , and the inner trunnion are a monolithic unit.3. The apparatus of claim 1 , wherein the inner trunnion has a substantially spherical shape.4. The apparatus of claim 3 , wherein the substantially spherical shape enables the inner trunnion to be retained within the inner shroud without a retainer.5. The apparatus of claim 1 , wherein the inner trunnion includes a centerline claim 1 , the curved surface having a convex profile relative to the centerline.6. The apparatus of claim 4 , further including a retainer to retain the inner trunnion within the inner shroud.7. The apparatus of claim 1 , wherein the curved surface of the inner trunnion prevents vibration-induced locking of a rotation of the airfoil about the radial axis.8. An apparatus to be coupled within a gas turbine engine claim 1 , the gas turbine engine defining an axial axis claim 1 , a radial axis and a circumferential axis ...

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27-04-2017 дата публикации

VTG LEVER POSITIVE DISPLACEMENT PRESS JOINT

Номер: US20170114658A1
Принадлежит:

A number of variations may include a product comprising: a vane lever comprising a first end, a second end, a top surface, and a bottom surface; an opening which extends through the second end and which is defined by an inner surface, and wherein a perimeter of the inner surface comprises a plurality of vertical flutes which extend a length of the inner surface and which are constructed and arranged to displace a material of a vane shaft. 1. A product comprising: a vane lever comprising a first end , a second end , a top surface , and a bottom surface , an opening which extends through the second end and which is defined by an inner surface , and wherein a perimeter of the inner surface comprises a plurality of vertical flutes which extend a length of the inner surface and which each include a cutting edge constructed and arranged to displace a material of a vane shaft when the vane lever is pressed onto the vane shaft.2. The product of wherein the opening further includes a radial lip which extends inward from a perimeter of a top edge of the inner surface and covers at least a portion of the opening.3. The product of wherein the radial lip includes a through hole.4. The product of further comprising a tab which extends approximately perpendicularly downward from the first end and which is constructed and arranged to mate with an adjustment ring of a vane pack assembly.5. The product of wherein the first end comprises a fork profile which is constructed and arranged to attach to an adjustment ring of a vane pack assembly.6. The product of wherein the fork profile includes a first and a second protrusion which are constructed and arranged to surround a pin attached to the adjustment ring.7. The product of further comprising a vane component comprising a vane shaft and a vane which rotates around the vane shaft claim 1 , and wherein the vane lever is pressed onto the vane shaft so that a material of the vane shaft is displaced.8. The product of wherein the vane shaft ...

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16-04-2020 дата публикации

TURBINE VANE, TURBINE BLADE, AND GAS TURBINE INCLUDING THE SAME

Номер: US20200116031A1
Принадлежит:

A turbine vane and a turbine blade are provided. Each of the turbine vane and the turbine blade may include a sidewall configured to form an airfoil and include a leading edge and a trailing edge, a partition wall configured to partition an internal space of the sidewall to form a plurality of cooling channels, and a metering plate configured to block inlet parts of the cooling channels and include cooling holes communicating with respective cooling channels. The metering plate may include a first cooling hole formed in the inlet part of each of the cooling channels and a second cooling hole formed, at a position close to the leading edge, in the inlet part of the cooling channel adjacent to the leading edge among the plurality of cooling channels. 1. A turbine vane comprising:a sidewall configured to form an airfoil and include a leading edge and a trailing edge;a partition wall configured to partition an internal space of the sidewall to form a plurality of cooling channels; anda metering plate configured to block inlet parts of the plurality of cooling channels and include cooling holes communicating with respective cooling channels,wherein the metering plate includes a first cooling hole formed in the inlet part of each of the plurality of cooling channels and a second cooling hole formed, at a position close to the leading edge, in the inlet part of the cooling channel adjacent to the leading edge among the plurality of cooling channels.2. The turbine vane according to claim 1 , wherein a cooling air drawn through the second cooling hole cools a leading edge region of the sidewall.3. The turbine vane according to claim 2 ,wherein the first cooling hole has a rectangular shape, andwherein the second cooling hole has a circular shape.4. The turbine vane according to claim 2 ,wherein the first cooling hole has a circular or an elliptical shape, andwherein the second cooling hole has a circular or an elliptical shape.5. The turbine vane according to claim 2 , ...

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14-05-2015 дата публикации

Drive Arrangement For A Unison Ring Of A Variable-Vane Assembly

Номер: US20150132111A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A variable-vane assembly has a nozzle ring supporting an array of pivotable vanes, and a unison ring for pivoting the vanes in unison. A crank mechanism rotatably drives the unison ring, and includes an external crank assembly positioned radially outward of the unison ring, a non-round drive block disposed in a non-round recess in an outer periphery of the unison ring, and a crank arm having a forked end connected to the drive block and an opposite end connected to the external crank assembly. The forked end defines two legs and the drive block is disposed between the legs and is pivotally connected to the legs such that the drive block is pivotable relative to the crank arm about a pivot axis. The crank mechanism is arranged such that the crank arm is caused to swing through an arc of movement, thereby rotating the unison ring. 1. A variable-vane assembly for a turbocharger , comprising:a nozzle ring having opposite first and second faces;a plurality of vanes adjacent the second face of the nozzle ring and having respective axles received into apertures in the nozzle ring and being rotatable in the apertures such that the vanes are rotatable about respective vane axes defined by the axles in the apertures, a distal end of each axle projecting out from the respective aperture beyond the first face;a plurality of vane arms respectively affixed rigidly to the distal ends of the axles, each vane arm having a free end;a unison ring positioned adjacent the nozzle ring with a first face of the unison ring opposing the first face of the nozzle ring, the unison ring being connected to the free ends of the vane arms, the unison ring being rotatable about a rotation axis so as to pivot the vane arms about the vane axes, thereby pivoting the vanes in unison; anda crank mechanism for rotatably driving the unison ring to pivot the vanes, the crank mechanism including an external crank assembly positioned radially outward of the unison ring, a non-round drive block disposed in a ...

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07-08-2014 дата публикации

INDIVIDUAL INLET GUIDE VANE CONTROL FOR TIP TURBINE ENGINE

Номер: US20140219772A1
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A tip turbine engine according to the present invention includes a plurality of independently variable inlet guide vanes for the fan and/or for the compressor. An actuator is operatively coupled to each of the flaps, such that each actuator can selectively vary the flap of its associated inlet guide vane. In one embodiment, the inlet guide vanes each include a pivotably mounted flap that is variable independently of the flaps of at least some of the other inlet guide vanes. In another embodiment, the inlet guide vanes each include at least one fluid outlet or nozzle directing pressurized air, as controlled by the associated actuator, to control inlet distortion. 1. A method for controlling a plurality of inlet guide vanes of a turbine engine , the method including the steps of:varying a first inlet guide vane of the plurality of inlet guide vanes to a first amount with a first actuator; andvarying a second inlet guide vane of the plurality of inlet guide vanes to a second amount with a second actuator while the first inlet guide vane is at the first amount, the first amount being different from the second amount, wherein the first actuator and the second actuator each independently control only one inlet guide vane.2. The method of wherein said step a) further includes the step of pivoting the first inlet guide vane to a first angle relative to a longitudinal axis through the turbine engine claim 1 , and said step b) further includes pivoting the second inlet guide vane to a second angle relative to the longitudinal axis while the first inlet guide vane is at the first angle claim 1 , the first angle being different from the second angle.3. The method of further including the step of varying the first angle and the second angle independently of one another.4. The method of wherein the plurality of inlet guide vanes are located radially inward of a bypass air flow path.5. The method of wherein the plurality of inlet guide vanes are mounted in a bypass air flow path.6 ...

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18-05-2017 дата публикации

STEAM TURBINE, CONTROL METHOD, AND PROGRAM

Номер: US20170138215A1
Принадлежит:

A steam turbine is provided with an electric motor, a plurality of controller units, a status storing unit, and a master controller. The electric motor drives a regulating valve for controlling the opening and closing of a steam passage in which steam supplied to a turbine body is circulated. The plurality of controller units control the drive of the electric motor. The status storing unit stores a parameter indicating a status of the steam turbine. When there is an abnormality in a controller unit that is controlling the drive of the electric motor, the master controller switches the controller unit to a controller unit among the controller units that is not controlling the electric motor, and causes the relevant controller unit to operate after rewriting the parameter to a parameter stored by the status storing unit before the abnormality had occurred. 1. A steam turbine , comprising:an electric motor which drives a regulating valve for regulating opening and closing of a steam passage through which steam supplied to a turbine body is circulated;a plurality of controller units which control drive of the electric motor;a status storing unit which stores a parameter indicating a status of the steam turbine; anda master controller which switches the controller unit to a controller unit among the controller units which is not controlling the electric motor in a case where there is an abnormality in the controller unit which controls the drive of the electric motor, and operates the controller unit after rewriting the parameter to a parameter stored by the status storing unit before the abnormality occurs.2. The steam turbine according to claim 1 ,wherein the status storing unit stores a turbine rotating speed which is detected in the turbine body serving as the parameter.3. The steam turbine according to claim 1 ,wherein the status storing unit stores a valve opening degree for controlling the regulating valve serving as the parameter.4. The steam turbine according to ...

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09-05-2019 дата публикации

Variable Turbine Geometry Vane Lever

Номер: US20190136709A1
Принадлежит: BORGWARNER INC.

A variable turbine geometry assembly is provided for controlling flow of exhaust gas to a turbine wheel of a turbocharger. The variable turbine geometry assembly includes a base structure, vanes, vane levers, and an adjustment ring. The vanes are distributed circumferentially around the base structure and are pivotable relative to the base structure to vary an effective inlet area. The vane levers are for pivoting the vanes. The vane levers each include an inner portion coupled to one of the vanes and an outer portion extending from the inner portion. The adjustment ring is selectively rotatable about a central axis to pivot the vanes. The adjustment ring includes apertures that are each associated with and have received therein the outer portion of one of the vane levers. The outer portion of each of the vane levers includes an outer surface that is non-parallel with the central axis. 1. A variable turbine geometry assembly for controlling flow of exhaust gas to a turbine wheel of a turbocharger , the variable turbine geometry assembly comprising:a base structure;vanes distributed circumferentially around the base structure and pivotable relative to the base structure to vary an effective inlet area;vane levers for pivoting the vanes, the vane levers each including an inner portion coupled to one of the vanes and an outer portion extending from the inner portion; andan adjustment ring that is selectively rotatable about a central axis to pivot the vanes, the adjustment ring including apertures that are each associated with and have received therein the outer portion of one of the vane levers;wherein the outer portion of each of the vane levers includes an outer surface that is non-parallel with the central axis.2. The variable turbine geometry assembly of claim 1 , wherein a cross-sectional area of the outer portion of each of the vane levers received in one of the apertures varies moving parallel with the central axis.3. The variable turbine geometry assembly of ...

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04-06-2015 дата публикации

TURBOCHARGER WITH VARIABLE TURBINE GEOMETRY HAVING GROOVED GUIDE VANES

Номер: US20150152741A1
Принадлежит: BORGWARNER INC.

A plurality of guide vanes (34) in a variable turbine geometry turbocharger (10) regulates a flow of exhaust gas. The guide vanes (34) are selectively adjustable between an open position to allow the flow of exhaust gas to drive a turbine wheel (24) and a closed position to block the flow of exhaust gas. A first flow feature (58) is disposed on first (44) and second (46) edges of the guide vanes (34) to disturb the flow of exhaust gas to prevent leakage of exhaust gas around the first (44) and second (46) edges. A second flow feature (64) is disposed on front (60) and rear (62) surfaces of the guide vanes (34) to channel the flow of exhaust gas between adjacent guide vanes (34) when the guide vanes (34) are in the open position to prevent swirling and/or cross flow of the exhaust gas. 13428241034. A guide vane () for regulating a flow of exhaust gas through a wheel inlet () to a turbine wheel () in a variable turbine geometry turbocharger () , said guide vane () comprising:{'b': 36', '54', '56', '36', '44', '46', '60', '62', '44', '28', '46', '28, 'a body () extending between a leading edge () and a trailing edge (), said body () including opposing first () and second () edges and opposing front () and rear () surfaces, wherein said first edge () is adjacent to one side of the wheel inlet () and said second edge () is adjacent to another side of the wheel inlet (); and'}{'b': 58', '64', '36', '34', '10, 'at least one flow feature (, ) disposed on said body () of said guide vane () for manipulating the flow of exhaust gas during use of the turbocharger ().'}234584446584446. The guide vane () as set forth in including a first flow feature () on at least one of said first () and second () edges claim 1 , wherein said first flow feature () prevents the flow of exhaust gas around said at least one of said first () and second () edges.3345854365636. The guide vane () as set forth in wherein said first flow feature () extends from said leading edge () of said body () to ...

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16-05-2019 дата публикации

High dynamic range video capture using variable lighting

Номер: US20190147571A1
Принадлежит: General Electric Co

A system and method is generally provided for producing a high dynamic range video. The system includes a probe and a computer communicatively coupled to the probe. The probe includes a camera and a light source. Further, the probe produces a plurality of frames. The computer includes at least one processor and at least one memory device. The memory device contains instructions configured to combine the plurality of frames into composite frames. The instructions are further configured to filter out portions of frames captured below a first threshold of light and portions of frames captured above a second threshold of light. The light source modulates a lighting characteristic, and the camera captures a first video with the modulated light source to produce a plurality of frames defining a plurality of lighting characteristics. Further, the computer combines the plurality of frames into a second video including a plurality of composite frames.

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07-06-2018 дата публикации

VANE POSITION SENSOR INSTALLATION WITHIN A TURBINE CASE

Номер: US20180156058A1
Принадлежит:

A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane. 1. A measuring system for sensing vane positions , comprising:a turbine including a plurality of articulating vanes, wherein each vane coupled to a sync ring, wherein the sync ring is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring;a target coupled to a first position within a first region, wherein the first position is associated with a first vane of the plurality of articulating vanes;a sensor coupled via a bracket to a second position within the first region, wherein the sensor is configured to detect an orientation of the target, wherein the orientation of the target corresponds to a vane position of the first vane.2. The measuring system of claim 1 , wherein the first region is a high temperature and high pressure zone between a turbine case wall of the turbine and a turbine platform of the turbine.3. The measuring system of claim 1 , wherein the first position is on a portion of the sync ring that is in association with a crank arm of the first vane.4. The measuring system of claim 1 , wherein the first position is in association with the bracket claim 1 ,wherein the target is in physical communication with the bracket via a target guide and retaining ring, andwherein the target is configured to slide with respect ...

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28-08-2014 дата публикации

FLIGHT GAS TURBINE WITH A FIRST ROTATABLE SHAFT

Номер: US20140241860A1
Автор: BURGHARDT Sascha
Принадлежит: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG

The present invention describes an aircraft gas turbine with a first rotatable shaft and a second shaft arranged coaxially thereto and which at least in an area close to the shaft end is non-rotatably connected to the first shaft. Recesses are provided in shaft areas at a distance from the connecting area between the shafts, said recesses overlapping one another at least in some areas when a defined twist of the first shaft relative to the second shaft is exceeded. The shafts are assigned at least one lever element designed rotatable and engaging in the recesses of the shafts in the radial direction in the area of an end of the shafts and swivelling about a pivot point. A second lever arm of the lever elements is, when the first lever arm is engaged in the recesses, operatively connectable to an electric sensor device, in the area of which a sensor signal equivalent to the defined twist of the first shaft can be generated. 1. Aircraft gas turbine with a first rotatable shaft , via which a torque can be exchanged between at least two assemblies , and a second shaft arranged coaxially thereto and which at least in an area close to the shaft end is non-rotatably connected to the first shaft , where recesses are provided in shaft areas at a distance from the connecting area between the shafts , said recesses overlapping one another at least in some areas when a twist of the first shaft relative to the second shaft , defined as a function of the torque applied in the area of the first shaft , is exceeded , where the shafts in the area of the recesses , are assigned at least one lever element designed rotatable about a pivot point fixed relative to the shaft and which engages in the recesses of the shafts in the radial direction in the area of an end of a lever arm , when there is a corresponding overlap of the recesses of the shafts , and swivels about the pivot point , with a radial distance between an end of a second lever arm of the lever element and the shafts ...

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04-09-2014 дата публикации

VARIABLE NOZZLE UNIT AND VARIABLE GEOMETRY SYSTEM TURBOCHARGER

Номер: US20140248137A1
Принадлежит: IHI CORPORATION

A variable geometry system turbocharger includes a variable nozzle unit, which is disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and which adjusts a passage area for the exhaust gas to be supplied to a turbine impeller. The bearing housing includes a container recessed portion which contains a link mechanism of the variable nozzle unit. 1: A variable geometry system turbocharger configured to supercharge air to be supplied to an engine side by using energy of an exhaust gas from the engine , comprisinga variable nozzle unit disposed in a turbine housing by being sandwiched between the turbine housing and a bearing housing, and configured to adjust a passage area for the exhaust gas to be supplied to a turbine impeller, wherein a first base ring disposed between a turbine scroll passage and the turbine impeller in the turbine housing, and concentrically with the turbine impeller;', 'a second base ring provided at a position away from and opposed to the first base ring in an axial direction of the turbine impeller, and integrally with the first base ring;', 'a plurality of variable nozzles disposed between facing surfaces of the first base ring and the second base ring, each variable nozzle being rotatable in forward and reverse directions about a pivot parallel to a pivot of the turbine impeller;', 'a link mechanism disposed on an opposite surface side of the first base ring from the facing surface thereof and configured to cause the plurality of variable nozzles to synchronously rotate in opening and closing directions; and', 'a support member provided integrally on the opposite surface of the first base ring from the facing surface thereof, the support member including an inner edge portion integrally joined to the opposite surface of the first base ring from the facing surface thereof, and an outer edge portion sandwiched by the turbine housing and the bearing housing, and wherein, 'the variable nozzle unit ...

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14-06-2018 дата публикации

VANE ACTUATING MECHANISM HAVING A LATERALLY MOUNTED ACTUATING LEVER

Номер: US20180163560A1
Автор: Mairhanser Vitalis
Принадлежит:

A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided. 114-. (canceled)15: A lever assembly forming part of a vane actuating mechanism of a turbomachine and serving to establish a link between a stator vane and an actuator , the lever assembly comprising:a lever and a U-shaped locking piece;the stator vane having a vane stem extending along a vertical axis and being connectable by the lever to an actuating ring of the actuator, the lever having has a jaw connecting portion, the lever being engageable via the jaw connecting portion with a contact portion of the vane stem; andthe U-shaped locking piece provided for locking the jaw connecting portion to the vane stem, the U-shaped locking piece having a passage opening formed in a main body allowing the U-shaped locking piece to be slid onto the vane stem and further having two legs extending from the main body at opposite ends, a first leg of the two legs being adapted for insertion into a jaw opening of the jaw connecting portion and a second leg being adapted for engagement with a mating surface of the jaw connecting portion, the mating surface being opposite the jaw opening; the jaw connecting portion and the locking piece being form-fittingly connected to the contact portion when in a locked position.16: The lever assembly as recited in wherein the connecting portion has opposing jaw faces and the contact portion has contact ...

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30-05-2019 дата публикации

VARIABLE NOZZLE MECHANISM AND ROTATING MACHINE INCLUDING THE SAME

Номер: US20190162075A1
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

A variable nozzle mechanism in which a nozzle mount has a first surface which has a minimum clearance in a direction of an axis with respect to a lever side facing surface in an opposing region facing the lever side facing surface in the direction of the axis, and a second surface which is disposed adjacent to the first surface in a circumferential direction of the nozzle mount and has a clearance in the direction of the axis with respect to the lever side facing surface larger than the clearance in the direction of the axis between the first surface and the lever side facing surface. 1. A variable nozzle mechanism , comprising:a first annular member;a plurality of nozzle vanes which are provided to face the first annular member, disposed in an annular fluid flow channel for guiding a working fluid from a scroll flow channel formed on an outer circumferential side of a turbine rotor to the turbine rotor, rotatable relative to the first annular member, and configured to adjust the flow passage area of the fluid flow channel;a plurality of vane shafts which are inserted through support holes penetrating through the first annular member and support the respective nozzle vanes one by one;a plurality of levers which are disposed outside the fluid flow channel and extend from the respective vane shafts radially outward of the first annular member; anda second annular member which is provided to be rotatable with respect to the first annular member around a central axis of the first annular member to support the plurality of levers, and rotates the nozzle vanes together with the levers relative to the first annular member,wherein each of the levers has a lever side facing surface which faces the first annular member in the direction of the central axis, andthe first annular member has a first surface which has a minimum clearance in the direction of the central axis with respect to the lever side facing surface in an opposing region that faces the lever side facing surface ...

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01-07-2021 дата публикации

NOZZLE VANE

Номер: US20210199020A1

A nozzle vane for a variable geometry turbocharger has an airfoil including a leading edge, a trailing edge, a pressure surface, and a suction surface at least in a center position in a blade height direction. The airfoil satisfies 0≤W/L<0.03, where Wis a maximum value of a distance from a line segment connecting the trailing edge and a fixed point on the pressure surface at a 40% chord position from the trailing edge toward the leading edge to a given point on the pressure surface between the trailing edge and the fixed point, and L is a length of the line segment. 1. A nozzle vane for a variable geometry turbocharger ,wherein the nozzle vane has an airfoil including a leading edge, a trailing edge, a pressure surface, and a suction surface at least in a center position in a blade height direction,{'sub': max', 'max, 'wherein the airfoil satisfies 0≤W/L<0.03, where Wis a maximum value of a distance from a line segment connecting the trailing edge and a fixed point on the pressure surface at a 40% chord position from the trailing edge toward the leading edge to a given point on the pressure surface between the trailing edge and the fixed point, and L is a length of the line segment, and'}wherein, in the airfoil, a camber line at an equal distance from the pressure surface and the suction surface is linear at least in a range from the trailing edge to a 40% chord position from the trailing edge toward the leading edge, the camber line includes a portion curved toward the pressure surface with respect to a chord line connecting the leading edge and the trailing edge between the leading edge and the trailing edge in a range from 40 to 100% chord positions, and the camber line does not intersect the chord line.2. The nozzle vane according to claim 1 ,wherein the nozzle vane has a hub-side edge and a tip-side edge, andwherein the nozzle vane has the airfoil at least in a region from 30 to 70% of a blade height from the hub-side edge in a direction from the hub-side edge ...

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02-07-2015 дата публикации

VARIABLE NOZZLE UNIT, VARIABLE GEOMETRY SYSTEM TURBOCHARGER, AND POWER TRANSMISSION MEMBER MANUFACTURING METHOD

Номер: US20150184534A1
Принадлежит: IHI CORPORATION

Power transmission members, such as synchronous joint members, are each formed by sintering a compact which is molded from a mixture containing metal powder and a binder, as an injection material, by metal powder injection molding. Flow promotion recesses configured to facilitate a flow of the mixture to areas corresponding to power transmission surfaces or the like when the compact is molded are formed in each of two side surfaces of each power transmission member. 1. A variable nozzle unit capable of varying a passage area for an exhaust gas to be supplied to a turbine impeller in a variable geometry system turbocharger , comprising:a base ring disposed concentrically with the turbine impeller inside a turbine housing in the variable geometry system turbocharger, and including a plurality of supporting holes formed to penetrate the base ring and arranged in a circumferential direction of the base ring; being rotatable about its axis parallel to an axis of the turbine impeller, and', 'including a nozzle shaft being integrally formed on a side surface of the variable nozzle on one side in an axial direction of the turbine impeller, and penetrating and being rotatably supported by the corresponding supporting hole in the base ring; and, 'a plurality of variable nozzles disposed on the base ring in a circumferential direction of the base ring in such a way as to surround the turbine impeller, each variable nozzle'}a link mechanism disposed on one side of the base ring in the axial direction, and configured to synchronously rotate the plurality of variable nozzles, a driving ring provided on the one side of the base ring in the axial direction, rotatably and concentrically with the base ring;', 'as many synchronous joint members as the variable nozzles, the synchronous joint members disposed on the driving ring in the circumferential direction of the driving ring, and each synchronous joint member having first power transmission surfaces on two sides in the ...

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13-06-2019 дата публикации

Verstellbare Turbomaschinenschaufel

Номер: US20190178100A1
Принадлежит:

A vane assembly including a variable vane (-) for a turbomachine is provided, the vane having at least one first, in particular plane or curved, engagement surface (′) for clamping, in particular without play, an actuator () of the vane assembly for adjustment of the vane, this first engagement surface not being inclined toward a longitudinal axis (L) of the vane or being inclined toward it by no more than 15°, and/or the vane assembly including a clamp () for clamping the actuator against the first engagement surface by at least partially elastically compressing the clamp transversely to the longitudinal axis of the vane and/or by advancing the clamp in a clamp direction (S) that forms an angle of at least 45° with the longitudinal axis of the vane. 115-. (canceled)16. A vane assembly comprising:a variable vane for a turbomachine, the vane having at least one first engagement surface for clamping an actuating means of the vane assembly for adjustment of the vane, the first engagement surface not being inclined toward a longitudinal axis of the vane or being inclined toward it by no more than 15°, or the vane assembly including a clamping means for clamping the actuating means against the first engagement surface by at least partially elastically compressing the clamping means transversely to the longitudinal axis of the vane or by advancing the clamping means in a clamping means direction forming an angle of at least 45° with the longitudinal axis of the vane.17. The vane assembly as recited in wherein the engagement surface is planar or curved and for clamping without play the actuating means.18. The vane assembly as recited in wherein the vane has at least one second engagement surface for clamping the actuating means claim 16 , the second engagement surface being inclined toward the first engagement surface claim 16 , the second engagement surface not being inclined toward the longitudinal axis of the vane or being inclined toward it by no more than 15° claim 16 ...

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22-07-2021 дата публикации

Vane And Shroud Arrangements For A Turbo-Machine

Номер: US20210222582A1
Автор: Shaw Christopher J.
Принадлежит:

A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The vanes are formed with a leading portion which is arranged to contact a leading portion of a corresponding slot, and a trailing portion which is shaped, when the leading portion of the vane and slot are together, to be spaced from a corresponding trailing portion of the slot with a substantially constant spacing at room temperature. The contact may be a point contact, e.g. close to the leading edge of the vane. Alternatively, the vane may include a leading surface portion which conforms closely with the shape of a corresponding leading surface portion of one of the slots. 1. A turbine comprising:(i) a turbine wheel having an axis,(ii) a turbine housing for defining a chamber for receiving the turbine wheel for rotation of the turbine wheel about an axis, the turbine housing further defining a gas inlet, and an annular inlet passage from the gas inlet to the chamber,(iii) a ring-shaped shroud defining a plurality of slots and encircling the axis, each slot having a slot surface; and(iv) a nozzle ring supporting a plurality of vanes which extend from the nozzle ring parallel to the axis, and project through respective ones of the slots;each of the vanes having:an axially-extending vane surface which includes (i) a vane outer surface facing a radially-outer surface of the corresponding slot, (ii) an opposed vane inner surface facing a radially-inner surface of the corresponding slot, anda median line between the vane inner surface and the vane outer surface extending from a leading end of the vane to a trailing end of the vane;the vane being positionable with a leading surface portion of the vane inner surface contacting a corresponding leading surface portion of the respective slot surface;the vane inner surface further including a trailing surface portion extending along at least 33% of the median line and, which, at ...

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14-07-2016 дата публикации

VARIABLE AREA TURBINE ARRANGEMENT WITH SECONDARY FLOW MODULATION

Номер: US20160201491A1
Принадлежит:

A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly. 1. A variable area turbine arrangement , comprising:a variable vane assembly;a secondary flow system associated with said variable vane assembly; andwherein flow modulation of a cooling fluid through said secondary flow system is changed simultaneously with actuation of said variable vane assembly.2. The variable area turbine arrangement as recited in claim 1 , wherein said variable vane assembly includes a spindle having a window and said secondary flow system includes a tube having a port configured to align with said window.3. The variable area turbine arrangement as recited in claim 2 , wherein said spindle is configured to rotate about a spindle axis to move said window relative to said port.4. The variable area turbine arrangement as recited in claim 3 , wherein said spindle is configured to rotate between a first position in which said port is covered by said spindle and a second position in which said port at least partially aligns with said window to permit a portion of said cooling fluid to enter said port.5. The variable area turbine arrangement as recited in claim 1 , wherein said variable vane assembly includes a spindle having a window and said secondary flow system includes a TOBI assembly having at least one passage that is selectively exposed to said window to alter an amount of said cooling fluid communicated through said secondary flow system.6. The variable area turbine arrangement as recited in claim 1 , wherein said variable vane assembly includes a spindle and said secondary flow system includes a TOBI assembly having at least one exit nozzle vane linked to said spindle through a linkage ...

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02-10-2014 дата публикации

Turbine for an exhaust gas turbocharger

Номер: US20140294576A1
Принадлежит: IHI Charging Systems International GmbH

In a turbine for an exhaust gas turbocharger with a turbine casing having receiving chamber for accommodating a turbine wheel and at least one volute through which the exhaust gas is guided via a feed passage into the receiving chamber and wherein at least one guide element is provided in the turbine casing so as to project into the feed passage in a guide region for guiding the exhaust gas onto the turbine wheel, the guide element comprises a first length region in the axial direction of the turbine, in which the guide element is designed with respect to its aerodynamic properties differently from its aerodynamic design in a second length region adjoining the first length region.

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28-07-2016 дата публикации

Translating Compressor and Turbine Rotors for Clearance Control

Номер: US20160215647A1
Автор: Smith Darren M.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance. 1. A spool for a gas turbine engine comprising:a compressor rotor, including a plurality of compressor blades each extending radially outwardly from the compressor rotor to an outer tip, and a compressor housing surrounding each of said compressor blade tips, with said compressor housing having an inner surface, and a compressor tip clearance defined between each of said compressor blade tips and said inner surface of said compressor housing, and a first actuator for moving said compressor rotor and said compressor blades along a rotational axis of said compressor rotor;a turbine rotor including a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip, and a turbine housing surrounding each of said turbine blade tips, with said turbine housing having an inner surface, and a turbine tip clearance defined between each of said turbine blade tips and said inner surface of said turbine housing, and a second actuator for moving said turbine rotor and said turbine blades along a rotational axis of said turbine rotor; anda control for controlling said first actuator of said compressor rotor, and for controlling said second actuator of said turbine rotor to control the compressor tip ...

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25-06-2020 дата публикации

LARGE-SCALE BYPASS FAN CONFIGURATION FOR TURBINE ENGINE CORE AND BYPASS FLOWS

Номер: US20200200080A1
Принадлежит: ROLLS-ROYCE PLC

A gas turbine engine for an aircraft includes an engine core including a turbine, a compressor, a core shaft, and a core exhaust nozzle, the core exhaust nozzle having a core exhaust nozzle pressure ratio calculated using total pressure at the core nozzle exit; a fan including a plurality of fan blades; and a nacelle surrounding the fan and the engine core and defining a bypass duct, the bypass duct including a bypass exhaust nozzle, the bypass exhaust nozzle having a bypass exhaust nozzle pressure ratio calculated using total pressure at the bypass nozzle exit; 2. The gas turbine engine of claim 1 , wherein the bypass to core ratio is in the range from 1.10 to 2.00 claim 1 , under aircraft cruise conditions.3. The gas turbine engine of claim 1 , wherein the bypass to core ratio is above 1.15 under aircraft cruise conditions.4. The gas turbine engine of claim 1 , wherein the fan has a fan tip radius claim 1 , and either:(i) the fan tip radius is in the range from 110 cm to 150 cm, and the bypass to core ratio is in the range from 1.1 to 1.4; or(ii) the fan tip radius is in the range from 155 cm to 200 cm, and the bypass to core ratio is in the range from 1.3 to 1.6.5. The gas turbine engine of claim 1 , wherein the total pressure at the bypass exhaust nozzle exit is determined at an exit plane of the bypass exhaust nozzle claim 1 , the exit plane extending from a rearmost point of the nacelle towards a centreline of the gas turbine engine.6. The gas turbine engine of claim 1 , wherein the engine core comprises a casing claim 1 , and wherein the total pressure at the core exhaust nozzle exit is determined at an exit plane of the core exhaust nozzle claim 1 , the exit plane extending from a rearmost point of the casing towards a centreline of the gas turbine engine.7. The gas turbine engine of claim 1 , wherein a flow area of the bypass exhaust nozzle is in the range from 2 mto 6 m.8. The gas turbine engine of claim 7 , wherein the fan has a fan tip radius claim 7 , ...

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04-07-2019 дата публикации

Controlled Flow Guides for Turbines

Номер: US20190203609A1
Автор: HALLER Brian Robert
Принадлежит: GENERAL ELECTRIC COMPANY

This application provides a steam turbine. The steam turbine may include a number of controlled flow runners and a number of controlled flow guides. The controlled flow guides may include an upstream passage ratio (W/W) of 0.4 to 0.7. 1. A steam turbine , comprising:a plurality of controlled flow runners; anda plurality of controlled flow guides;{'sub': 'up', 'the plurality of controlled flow guides comprising an upstream passage ratio (W/W) of 0.4 to 0.7.'}2. The steam turbine of claim 1 , wherein the upstream passage ratio (W/W) comprises about 0.63. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a pitch to width ratio of more than 1.9.4. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a suction side acceleration rate of −0.05 to −0.25 bar/mm.5. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a suction side acceleration rate of about −0.2 bar/mm.6. The steam turbine of claim 1 , wherein each of the plurality of controlled flow guides comprises a throat.7. The steam turbine of claim 6 , wherein the plurality of controlled flow guides comprises a Mach number distribution (M/M) upstream of the throat of more than 1.01.8. The steam turbine of claim 6 , wherein the plurality of controlled flow guides comprises a Mach number distribution upstream (M/M) of the throat of about 1.07.9. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a deflection angle of between 25 degrees to 38 degrees.10. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a deflection angle of about 30 degrees.11. The steam turbine of claim 1 , wherein the plurality of controlled flow guides is attached to a casing.12. The steam turbine of claim 1 , wherein the plurality of controlled flow guides comprises a plurality of first stage controlled flow guides.13. The steam turbine of claim 1 , wherein the ...

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13-08-2015 дата публикации

GRID VALVE ASSEMBLY

Номер: US20150226089A1
Принадлежит: DRESSER-RAND COMPANY

A grid valve assembly for a steam turbine is provided. The grid valve assembly may include an annular stationary member disposed between an upstream stage and a downstream stage of the steam turbine. The annular stationary member may define a plurality of stationary member openings extending radially therethrough from an outer circumferential surface to an inner circumferential surface thereof. The grid valve assembly may also include an annular rotatable member rotatably disposed about the outer circumferential surface of the annular stationary member. The annular rotatable member may define a plurality of rotatable member openings extending radially therethrough. 1. A grid valve assembly for a steam turbine , comprising:an annular stationary member disposed between an upstream stage and a downstream stage of the steam turbine, the annular stationary member defining a plurality of stationary member openings extending radially therethrough from an outer circumferential surface to an inner circumferential surface thereof; andan annular rotatable member rotatably disposed about the outer circumferential surface of the annular stationary member and defining a plurality of rotatable member openings extending radially therethrough.2. The grid valve assembly of claim 1 , wherein the annular stationary member includes a flange extending radially outward from a first axial end portion thereof and configured to couple the annular stationary member with a casing of the steam turbine.3. The grid valve assembly of claim 2 , wherein the annular stationary member includes a lip extending radially outward from a second axial end portion thereof.4. The grid valve assembly of claim 3 , wherein the annular rotatable member is rotatably disposed about the outer circumferential surface of the annular stationary member between the flange and the lip claim 3 , and the flange and the lip are configured to maintain an axial alignment of the annular rotatable member relative to the annular ...

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09-08-2018 дата публикации

FUEL CONTROL DEVICE, COMBUSTOR, GAS TURBINE, CONTROL METHOD, AND PROGRAM

Номер: US20180223743A1
Принадлежит:

An IGV opening command value is corrected to calculate an actual opening equivalent value that indicates an approximate value of an actual opening. A temperature estimation value, for a case where a mixture of fuel and in-flowing air is combusted, is calculated using the actual opening equivalent value, atmospheric conditions, and an output from a gas turbine. A fuel distribution command value that indicates distribution of fuel output from a plurality of fuel supply systems is calculated on the basis of the temperature estimation value. The fuel distribution command value and a fuel control signal command value that indicates the total flow rate of fuel to be output to the plurality of fuel supply systems are acquired, and respective valve openings of fuel flow rate regulating valves of the fuel supply systems are calculated on the basis of the fuel distribution command value and the fuel control signal command value. 1. A fuel control device comprising:an IGV response correction unit configured to correct an opening command value of an inlet guide vane, which controls an amount of air caused to be mixed and combust with fuel, and, to calculate an actual opening equivalent value that indicates an approximate value of an actual opening, when an opening-closing operation of the inlet guide vane is performed on the basis of the opening command value;a combustion temperature estimation value calculation unit configured to calculate a temperature estimation value when a mixture of the fuel and in-flowing air is combusted, using the actual opening equivalent value, atmospheric conditions, and a gas turbine output;a fuel distribution command value calculation unit configured to calculate and output, on the basis of the temperature estimation value, a fuel distribution command value that indicates a distribution of the fuel output from a plurality of fuel supply systems; anda valve opening calculation unit configured to acquire the fuel distribution control signal and a ...

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19-08-2021 дата публикации

VARIABLE STATOR VANE AND METHOD OF FABRICATING VARIABLE STATOR VANE

Номер: US20210254493A1
Принадлежит: ROLLS-ROYCE PLC

The present disclosure relates to a variable stator vane and a method of fabricating the variable stator vane of a gas turbine engine. The method includes providing at least one fibre sheet. The method further includes rolling the at least one fibre sheet around a mandrel to form a spindle section of the variable stator vane. An excess of material of the at least one fibre sheet remains after forming the spindle section. The method further includes using the excess of material of the at least one fibre sheet to form the at least one aerofoil section of the variable stator vane. 1. A method of fabricating a variable stator vane , the method comprising:providing at least one fibre sheet;rolling the at least one fibre sheet around a mandrel to form a spindle section of the variable stator vane, wherein an excess of material of the at least one fibre sheet remains after forming the spindle section; andusing the excess of material of the at least one fibre sheet to form at least one aerofoil section of the variable stator vane.2. The method of claim 1 , wherein rolling the at least one fibre sheet around the mandrel comprises rolling a plurality of turns of the fibre sheet around the mandrel.3. The method of claim 1 , further comprising wrapping the excess of material of the at least one fibre sheet around one or more inserts.4. The method of claim 1 , wherein rolling the at least one fibre sheet around the mandrel comprises rolling a turn of the fibre sheet around an insert so that the insert is disposed between two adjacent turns of the spindle section.5. The method of claim 1 , further comprising providing a further fibre sheet over the spindle section and the at least one aerofoil section to provide an outer layer of the variable stator vane.6. The method of claim 1 , wherein using the excess of material further comprises pressing the excess of material of the at least one fibre sheet between a female aerofoil tool and a male aerofoil tool.7. The method of claim 1 , ...

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30-10-2014 дата публикации

GUIDE APPARATUS FOR A TURBINE OF AN EXHAUST GAS TURBOCHARGER

Номер: US20140321991A1
Принадлежит:

In a guide apparatus for a turbine of an exhaust gas turbocharger with a first insert part and a second insert part arranged opposite the first insert part and with at least one first guide vane for deflecting exhaust gas flowing through the turbine, which is arranged between the insert parts and rotatably supported on at least one of the insert parts so as to be rotatable about an axis of rotation relative to the insert parts, at least one second guide vane for deflecting the exhaust gas is provided which is immovable relative to the insert parts. 110151618161216181618201618141618. A guide apparatus () for a turbine of an exhaust gas turbocharger with an insert element () comprising a first insert part () and second insert part () arranged opposite the first insert part () and with at least one first guide vane () for deflecting exhaust gas flowing through the turbine arranged between the insert parts ( , ) and rotatably supported on at least one of the insert parts ( , ) so as to be rotatable about an axis of rotation () relative to the insert parts ( , ) , and at least one second guide vane () for deflecting the exhaust gas mounted immovably between the insert parts ( , ).210161814. The guide apparatus () according to claim 1 , wherein at least one of the first and second insert parts ( claim 1 , ) and the second guide vane () are at least partially integrally formed with one another.310161814. The guide apparatus () according to claim 2 , wherein the at least one of the first and second insert part ( claim 2 , ) and the second guide vane () are formed jointly cast.410122220161812261618. The guide apparatus () according to claim 1 , wherein the first guide vane () is supported via at least one bearing element () which is rotatable about the axis of rotation () relative to the insert parts ( claim 1 , ) claim 1 , is separately formed from the first guide vane () and at least partially accommodated in an opening () of the at least one of the insert parts ( claim 1 ...

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23-08-2018 дата публикации

NOZZLE DRIVE MECHANISM AND TURBOCHARGER

Номер: US20180238190A1
Принадлежит: IHI CORPORATION

Provided is a nozzle drive mechanism, including: a bearing; a drive shaft inserted into a bearing hole; and a link plate having an opposing portion, which is opposed to at least the bearing in an axial direction of the drive shaft, and is subjected to hardening treatment, the link plate being fixed to the drive shaft by caulking, bolt-fastening, or press-fitting. 1. A nozzle drive mechanism , comprising:a bearing;a drive shaft inserted into the bearing; anda link plate having an opposing portion, which is opposed to at least the bearing in an axial direction of the drive shaft, and is subjected to hardening treatment, the link plate being fixed to the drive shaft by caulking, bolt-fastening, or press-fitting.2. A nozzle drive mechanism according to claim 1 , further comprising:an insertion hole, which is formed in the link plate, and is configured to receive the drive shaft to be inserted into the insertion hole; andan insertion portion to be inserted into the insertion hole, which is formed at a distal end portion of the drive shaft, and is caulked at a part of the insertion portion projecting from the insertion hole.3. A nozzle drive mechanism according to claim 2 , wherein the drive shaft is subjected to the hardening treatment at a portion other than the insertion portion.4. A nozzle drive mechanism according to claim 2 , wherein the drive shaft comprises:a large-diameter portion which has an outer diameter larger than an outer diameter of the insertion portion; anda step surface, which extends in a radial direction of the drive shaft from an outer peripheral surface of the insertion portion to an outer peripheral surface of the large-diameter portion, and is opposed to the link plate in an axial direction of the drive shaft.5. A nozzle drive mechanism according to claim 3 , wherein the drive shaft includes:a large-diameter portion which has an outer diameter larger than an outer diameter of the insertion portion; anda step surface, which extends in a radial ...

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30-07-2020 дата публикации

Steam turbine system

Номер: US20200240271A1

A steam turbine system 1 includes a steam turbine 10including a plurality of rotor blades 16; a first mixed steam supply pipe 21 that supplies the steam, which is supplied from a steam supply source 40 capable of supplying the steam with fluctuating pressure, to an upstream stage Sa within the casing 11; a second mixed steam supply pipe 22 that supplies the steam to the second stepped part Sb; an adjusting unit 25 that adjusts a flow rate of the steam supplied to the first stepped part Sa and the second stepped part Sb; and a control unit 30 that controls the adjusting unit 25 on the basis of a differential pressure between a pressure P0 of the steam supplied from the steam supply source 40 and a pressure in the first stepped part Sa.

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30-07-2020 дата публикации

GUIDE VANE CASCADE FOR A TURBOMACHINE

Номер: US20200240283A1
Автор: BRIGNOLE Giovanni
Принадлежит: MTU Aero Engines AG

The present invention relates to a guide vane cascade for a turbomachine, which has guide vanes that are mounted adjustably about an axis of rotation, so as to change an inflow angle each time, wherein a first guide vane and a second guide vane arranged on the pressure side thereof, referred to a longitudinal axis of the turbomachine, are arranged with an axial offset, namely, the axis of rotation of the second guide vane is offset axially toward the back, wherein the first guide vane and the second guide vane are provided such that, in an adjusted state, they form together a tandem configuration in a radially outer region but together they delimit a divergent channel in a radially inner region. 1. A guide vane cascade for a turbomachine , comprising:guide vanes that are mounted adjustably about an axis of rotation, so as to change an inflow angle each time,wherein a first guide vane and a second guide vane arranged on the pressure side thereof referred to a longitudinal axis of the turbomachine are arranged with an axial offset, namely, the axis of rotation of the second guide vane is offset axially toward the back,wherein the first guide vane and the second guide vane are provided such that, in an adjusted state, they form together a tandem configuration in a radially outer region; and together they delimit a divergent channel in a radially inner region.2. The guide vane cascade according to claim 1 , wherein the first and the second guide vanes differ in their vane body profile in at least one of the regions.3. The guide vane cascade according to claim 2 , wherein the first guide vane has a longer camber line than the second guide vane in the radially outer region.4. The guide vane cascade according to claim 3 , wherein the camber line of the first guide vane is at least 20% longer than the camber line of the second guide vane in the radially outer region.5. The guide vane cascade according to claim 2 , wherein the second guide vane has a longer camber line than ...

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18-11-2021 дата публикации

METHOD FOR CONTROLLING AND LIMITING A SPEED OF A TURBOCHARGER

Номер: US20210355842A1
Принадлежит: VOLKSWAGEN AKTIENGESELLSCHAFT

A method for controlling a speed of a turbocharger that is in operative connection with a compressor, the steps including: provision of a setpoint for the speed of the turbocharger on the basis of a model-based precontrol for a calculation of a desired boost pressure ahead of the turbocharger; determination of an actual value for the speed of the turbocharger; control of an actuator of the turbocharger in order to compensate for the difference between the desired value and the actual value for the speed of the turbocharger. Amain signal and a subsidiary signal are provided during the determination of the actual value for the speed of the turbocharger, wherein the main signal and the subsidiary signal are combined in order to validate the actual value for the speed of the turbocharger. 1. A method for controlling a speed of a turbocharger that is in operative connection with a compressor , the method comprising:providing a setpoint for the speed of the turbocharger on the basis of a model-based precontrol for a calculation of a desired boost pressure ahead of the turbocharger;determining an actual value for the speed of the turbocharger;controlling an actuator of the turbocharger to compensate for a difference between the desired value and the actual value for the speed of the turbocharger; andproviding a main signal and a subsidiary signal during the determination of the actual value for the speed of the turbocharger, wherein the main signal and the subsidiary signal are combined in order to validate the actual value for the speed of the turbocharger.2. The method according to claim 1 , wherein a minimum threshold and a maximum threshold are calculated from the main signal in the determination step claim 1 , wherein a leakage factor is produced as a function of the subsidiary signal claim 1 , the minimum threshold and the maximum threshold.3. The method according to claim 2 , wherein the leakage factor equal to 0 is produced if the subsidiary signal is less than a ...

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15-10-2015 дата публикации

TURBOEXPANDER AND DRIVEN TURBOMACHINE SYSTEM

Номер: US20150292349A1
Принадлежит:

A turboexpander and driven turbomachine system comprising a turboexpander configured for expanding a first fluid and comprising an expander stage with one expander impeller; a first set of moveable inlet guide vanes at the inlet of the expander stage; a driven turbomachine configured for processing a second fluid and comprising a turbomachine impeller; a second set of moveable inlet guide vanes at the inlet of the turbomachine impeller; a mechanical transmission between the turboexpander and the driven turbomachine; and a controller connected to the second set of moveable inlet guide vanes and configured for controlling the second set of moveable inlet guide vanes for adjusting the rotary speed of the driven turbomachine and said turboexpander. 1. A turboexpander and driven turbomachine system comprising:a turboexpander configured to expand a first fluid, and comprising at least one expander stage with an expander impeller;at least one first set of moveable inlet guide vanes at an inlet of the at least one expander stage;a driven turbomachine configured to process a second fluid, different from the first fluid, and comprising at least one turbomachine impeller;a second set of moveable inlet guide vanes at an inlet of the at least one turbomachine impeller;a mechanical transmission between the turboexpander and the driven turbomachine; anda controller connected to the second set of moveable inlet guide vanes, wherein the controller is configured to control the second set of moveable inlet guide vanes to adjust a rotary speed of the turboexpander and the driven turbomachine, to receive information on the rotary speed and, and to control the second set of moveable inlet guide vanes to adjust the rotary speed at a desired speed value.2. The system according to claim 1 , wherein the at least one first set of moveable inlet guide vanes is configured to control at least one parameter of the first fluid.3. The system according to claim 2 , wherein the at least one parameter ...

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10-09-2020 дата публикации

Distributed Control Modules with Cumulating Command References

Номер: US20200285207A1
Принадлежит:

A distributed control system may include a main processing unit, a distributed control module, and a controllable component. The distributed control module may be configured to receive a nominal command reference from the main processing unit, determine a series of cumulating command references based at least in part on the nominal command reference; and output a series of cumulating control commands to the controllable component. The series of cumulating control commands may be based at least in part on the series of cumulating command references. 1. A method of controlling a controllable component , the method comprising:receiving a nominal command reference from a main processing unit;determining a series of cumulating command references based at least in part on the nominal command reference; andoutputting a series of cumulating control commands to a controllable component, the series of cumulating control commands based at least in part on the series of cumulating command references.2. The method of claim 1 , wherein determining the series of cumulating command references comprises:determining a command reference reciprocal (K), wherein (K) represents a real number;determining a series of K(t)-incremental command references sequentially corresponding to one of (K)-increments of a DCM unit time interval (t), wherein (t) represents a unit of time of a DMC clock, and wherein K(t) represents (K) increments as a function of (t); anddetermining a series of K(t)-cumulating command references sequentially corresponding to one of the (K)-increments of the DCM unit time interval (t), the series of K(t)-cumulating command reference determined based at least in part on the series of K(t)-incremental command references.3. The method of claim 2 , wherein determining the series of K(t)-incremental command references comprises:delaying the nominal command reference by a delay line, the delay line comprising a series of (K)-unit delay operators, the series of (K)-unit delay ...

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05-11-2015 дата публикации

RECOVERING SPEED IN DRIVELINE ASSEMBLY

Номер: US20150315928A1
Принадлежит: GENERAL ELECTRIC COMPANY

Aspects of the disclosure include apparatuses and program products for recovering speed in a driveline assembly. An apparatus in one embodiment may include: a sensor measuring a shaft speed of a rotatable shaft within a driveline assembly, wherein the driveline assembly includes: a load coupled to the rotatable shaft, a primary power source coupled to the load through the rotatable shaft to deliver a first power output to the load, and a secondary power source coupled to the load through the rotatable shaft to deliver a second power output to the load, wherein the second power output is less than the first power output; and a controller in communication with the secondary power source and the sensor, wherein the controller increases the second power output in response to the shaft speed being less than a minimum speed threshold. 1. An apparatus comprising: a load coupled to the rotatable shaft,', 'a primary power source coupled to the load through the rotatable shaft to deliver a first power output to the load, and', 'a secondary power source coupled to the load through the rotatable shaft to deliver a second power output to the load, wherein the second power output is less than the first power output; and, 'a sensor measuring a shaft speed of a rotatable shaft within a driveline assembly, wherein the driveline assembly includesa controller in communication with the secondary power source and the sensor, wherein the controller increases the second power output in response to the shaft speed being less than a minimum speed threshold.2. The apparatus of claim 1 , wherein the secondary power source comprises a motor claim 1 , and the controller is further configured to modify a power set point of the motor.3. The apparatus of claim 1 , wherein the driveline assembly further includes a torque converter coupled to the secondary power source and the rotatable shaft claim 1 , and the controller further modifies a conversion factor of the torque converter to increase or ...

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05-11-2015 дата публикации

ASYMMETRIC ACTUATOR PIVOT SHAFT BUSHING FOR VTG TURBOCHARGER

Номер: US20150315964A1
Принадлежит: BORGWARNER INC.

A turbocharger () includes a housing () and an actuating mechanism () for actuating a device () within the housing (). A pivot shaft () has an inside end () inside the housing () and an outside end () outside the housing (). The pivot shaft () is rotatably mounted in a bore () in the housing () for transmitting an actuating movement from outside the housing () to the actuating mechanism (). A bushing () is disposed in the bore (). The bushing () includes an asymmetric portion () that extends inside the housing () to support the inside end () of the pivot shaft (). 110. A turbocharger () comprising:{'b': 12', '14', '16, 'a turbocharger housing (, , );'}{'b': 46', '40', '12', '14', '16, 'an actuating mechanism () for actuating a device () within said turbocharger housing (, , );'}{'b': 42', '48', '12', '14', '16', '82', '12', '14', '16', '42', '64', '12', '14', '16', '12', '14', '16', '46, 'a pivot shaft () having an inside end () inside said turbocharger housing (, , ) and an outside end () outside said turbocharger housing (, , ), wherein said pivot shaft () is rotatably mounted in a bore () in said turbocharger housing (, , ) for transmitting an actuating movement from outside said turbocharger housing (, , ) to said actuating mechanism (); and'}{'b': 62', '64', '62', '68', '12', '14', '16', '48', '42, 'a bushing () disposed in said bore (), said bushing () including an asymmetric portion () extending inside said turbocharger housing (, , ) to support said inside end () of said pivot shaft ().'}210687868464262. The turbocharger () as set forth in wherein said asymmetric portion () is semi-cylindrical claim 1 , and wherein clearance is provided in a circumferential direction between edges () of said asymmetric portion () and said actuating mechanism () to allow rotation of said pivot shaft () relative to said bushing ().31062666466426842. The turbocharger () as set forth in wherein said bushing () includes a first portion () that is disposed in said bore () claim 2 ...

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01-11-2018 дата публикации

Joint Cover with Improved Manifold Block for Duct Leak Detection System

Номер: US20180313219A1
Принадлежит:

A manifold assembly configured for integration with a joint cover apparatus in a ducting system to detect leaking gas comprises an elastomeric manifold block having a substantially circular inlet aperture and one or more gas passages fluidly coupled to the inlet aperture. The assembly includes a flow control valve configured to maintain a closed state in which a component of the flow control valve sealingly engages with the inlet aperture to preclude gas at the inlet aperture from flowing into the one or more gas passages until said gas reaches a pressure corresponding to a pressure threshold. The assembly also includes at least one aperture control plate disposed substantially proximate to a lower end of the manifold block and including a substantially circular opening. The aperture control plate is adapted to maintain the substantial circularity of the inlet aperture, so as to ensure a substantially fluid-tight seal. 1. A manifold assembly configured for integration with a joint cover apparatus in a ducting system to detect leaking gas , the manifold assembly comprising:an elastomeric manifold block having a substantially circular inlet aperture and one or more gas passages having upper ends and fluidly coupled to the inlet aperture, wherein the upper ends of said one or more gas passages are configured to direct leaking gas toward one or more respective gas detectors;a flow control valve disposed within the manifold block between the inlet aperture and the one or more gas passages, said flow control valve configured to maintain a closed state in which a component of the flow control valve sealingly engages with the inlet aperture to preclude gas at the inlet aperture from flowing into the one or more gas passages until said gas reaches a pressure corresponding to a pressure threshold; andat least one aperture control plate having a substantially circular opening, said at least one aperture control plate being disposed substantially proximate to a lower end of the ...

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22-11-2018 дата публикации

NOZZLE BLADE DESIGN FOR A VARIABLE NOZZLE TURBINE

Номер: US20180334920A1
Автор: Hu Leon, Yi Jianwen James
Принадлежит:

Systems are provided for a nozzle blade for a variable nozzle turbine of a turbocharged engine. In one example, a nozzle blade for a turbine nozzle of a variable geometry turbine may include: a cambered outer surface that curves from an inlet end to an outlet end of the nozzle blade, relative to a chord of the nozzle blade, the chord having a chord length defined from the inlet end to the outlet end, the nozzle blade having an aspect ratio in a range of 1.54 to 2.95, a thickness that is greatest in a range of 47 to 61% of the chord length, and a camber line angle change ratio in a range of 0.94 to 1.16 from the inlet end to the outlet end of the nozzle blade. 1. A nozzle blade for a turbine nozzle of a variable geometry turbine , comprising:a cambered outer surface that curves from an inlet end to an outlet end of the nozzle blade, relative to a chord of the nozzle blade, the chord having a chord length defined from the inlet end to the outlet end, the nozzle blade having an aspect ratio in a range of 1.54 to 2.95, a thickness that is greatest in a range of 47% to 61% of the chord length.2. The nozzle blade of claim 1 , wherein the nozzle blade has a camber line angle change ratio in a range of 0.94 to 1.16 from the inlet end to a peak blade angle of the nozzle blade.3. The nozzle blade of claim 2 , wherein the camber line angle change ratio increases from the inlet end to a normalized distance of about 53% of the chord length claim 2 , then decreases until about 90% of the chord length claim 2 , and then increases again to the outlet end.4. The nozzle blade of claim 1 , wherein a pivot axis of the nozzle blade is positioned at a location in a range of 30% to 50% of the chord length from the inlet end to the outlet end of the nozzle blade.5. The nozzle blade of claim 1 , wherein a rate of change of the camber line angle change ratio is greatest between the inlet end of the nozzle blade and a mid-section of the blade along the chord length.6. The nozzle blade of ...

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17-12-2015 дата публикации

SINGLE BOLTING FLANGE ARRANGEMENT FOR VARIABLE GUIDE VANE CONNECTION

Номер: US20150361820A1
Принадлежит:

A single bolting flange arrangement for variable inlet guide vane (VIGV) connection includes a connection arm connected to a stem of the VIGV to rotate the VIGV. The connection arm is driven by a drive pin received in a slot of the connection arm. The connection arm has a bolting flange and the stem of the VIGV is fastened to one side of the single bolting flange by a bolt/nut assembly. 1. A variable guide vane (VGV) apparatus comprising:a plurality of variable guide vanes (VGVs), each vane having a rotational axis and being rotatable in an adjustable angular orientation about the rotational axis of the vane;a unison ring defining a central axis and including a plurality of drive pins affixed to the unison ring, the drive pins with the unison ring being adjustable in an angular orientation about the central axis;a plurality of arms each including a base, a pair of parallel forks extending away from the base in a first direction and a bolting flange extending away from the base in a second direction opposite to the first direction, the pair of forks defining a slot therebetween, one of said drive pins being slidably received in the slot, the bolting flange defining a hole extending therethrough;a plurality of stems connected to the respective VGVs and rotatable about the rotational axis of the respective vanes, each stem having an end section defining parallel side surfaces facing away from each other, each stem defining a hole extending from one side surface to the other side surface; anda plurality of bolts moveably securing the stems to the respective arms, each bolt extending in a tangential direction with respect to the central axis through the hole of one of the bolting flanges and through the hole of one of the stems, wherein one of the side surface of each stem is in contact with the bolting flange of a corresponding arm while the other side surface of each stem is free of contact with said corresponding arm.2. The apparatus as defined in further comprising a ...

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20-12-2018 дата публикации

VANE POSITION SENSOR INSTALLATION WITHIN A TURBINE CASE

Номер: US20180363490A1
Принадлежит:

A measuring system for sensing vane positions that comprises a turbine, a target, and a sensor. The turbine includes a plurality of articulating vanes, with each vane being coupled to a sync ring that is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring. The target is coupled to a first position of the turbine within a first region that is associated with a first vane of the plurality of articulating vanes. The sensor is coupled via a bracket to a second position of the turbine within the first region. The sensor is configured to detect an orientation of the target that corresponds to a vane position of the first vane. 1. A measuring system for sensing vane positions , comprising:a turbine including a plurality of articulating vanes, wherein each vane coupled to a sync ring, wherein the sync ring is configured to position the plurality of articulating vanes in accordance with a degree of rotation by the sync ring;a target coupled to a first position within a first region, wherein the first position is associated with a first vane of the plurality of articulating vanes;a sensor coupled via a bracket to a second position within the first region, wherein the sensor is configured to detect an orientation of the target, wherein the orientation of the target corresponds to a vane position of the first vane.2. The measuring system of claim 1 , wherein the first region is a temperature and pressure zone between a turbine case wall of the turbine and a turbine platform of the turbine.3. The measuring system of claim 1 , wherein the first position is in association with the bracket claim 1 ,wherein the target is in physical communication with the bracket via a target guide and retaining ring, andwherein the target is configured to slide with respect to a vane pin that is in contact with a surface of the first vane.4. The measuring system of claim 1 , wherein the turbine is a jet engine turbine employed by an ...

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19-11-2020 дата публикации

TURBINE AND TURBOCHARGER

Номер: US20200362721A1

A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller and including a scroll passage positioned on an outer circumferential side of the turbine impeller; a nozzle vane disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; a plate disposed on a side of the intermediate flow passage with respect to an inner circumferential wall part of the housing, defining an inner circumferential boundary of the scroll passage, so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction; and at least one guide vane disposed in the gap between the inner circumferential wall part and the plate in the axial direction. The at least one guide vane includes: a first end; and a second end disposed radially on an outer side of the first end and circumferentially downstream of the first end in the exhaust gas flow direction. 1. A turbine , comprising:a turbine impeller;a housing disposed so as to enclose the turbine impeller, the housing including a scroll passage positioned on an outer circumferential side of the turbine impeller;a nozzle vane disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller;a plate disposed on a side of the intermediate flow passage with respect to an inner circumferential wall part of the housing so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction, the inner circumferential wall part defining an inner circumferential boundary of the scroll passage; andat least one guide vane disposed in the gap between the inner circumferential wall part and the plate in the axial ...

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26-12-2019 дата публикации

FLOW CONTROL NOZZLE

Номер: US20190390562A1
Принадлежит:

There is disclosed a flow control nozzle for controlling the flow of an incompressible fluid, the flow control nozzle having a flow area and comprising a deformable element comprising a shaped memory alloy (SMA) material wherein within a range of operating temperatures the SMA material is configured to reduce the flow area of the flow control nozzle as the operating temperature increases. The flow control nozzle is thus able to dynamically compensate for changes in operating temperature in order to maintain a constant flow. 1. A flow control nozzle for controlling the flow of an incompressible fluid , the flow control nozzle having a flow area and comprising a deformable element comprising a shaped memory alloy (SMA) material wherein within a range of operating temperatures the SMA material is configured to reduce the flow area of the flow control nozzle as the operating temperature increases.2. The flow control nozzle of wherein the SMA material is configured to reduce the flow area of the flow control nozzle as the operating temperature increases in order to maintain a substantially constant flow rate over the range of operating temperatures.3. The flow control nozzle of claim 1 , wherein the flow area comprises a flow passage claim 1 , wherein the flow passage is defined at least in part by the deformable element claim 1 , and wherein the SMA material is configured to reduce a dimension of the flow passage to reduce the flow area.4. The flow control nozzle of claim 1 , wherein the flow area comprises a flow passage claim 1 , and wherein the deformable element is disposed within the flow area so that fluid flows around the deformable element through the flow passage claim 1 , and wherein the deformable element deforms as the temperature increases to reduce the flow area.5. The flow control nozzle of wherein the SMA material is configured to reduce the flow area of the flow control nozzle according to a predetermined relationship for laminar flow conditions to ...

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24-12-2008 дата публикации

Exhaust gas turbocharger for a motor vehicle

Номер: DE202008011150U1
Автор: [UNK]

Abgasturbolader für ein Kraftfahrzeug, mit einem, ein Turbinerad umgehenden Bypass, welcher durch ein, von einer Stelleinrichtung steuer-/regelbares Wastegateventil regulierbar ist, dadurch gekennzeichnet, – dass ein im Wesentlich lineares Verbindungselement (2) vorgesehen ist, das über einen ersten Anbindungspunkt mit der Stelleinrichtung und über einen zweiten Anbindungspunkt mit dem Wastegateventil verbunden ist, – dass im Bereich des Verbindungselementes (2) und/oder dessen Anbindungspunkten zumindest eine Schnellfixiereinrichtung (1) vorgesehen ist, über die ein Abstand zwischen den beiden Anbindungspunkten einstell- und fixierbar ist. Exhaust gas turbocharger for a motor vehicle, having a bypass which bypasses a turbine wheel and which can be regulated by a wastegate valve which can be controlled by an actuating device, characterized, That a substantially linear connecting element (2) is provided, which is connected via a first connection point with the adjusting device and via a second connection point with the wastegate valve, - That in the region of the connecting element (2) and / or its connection points at least one Schnellfixiereinrichtung (1) is provided, via which a distance between the two connection points can be set and fixed.

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28-01-2010 дата публикации

Abgasturbolader für ein Kraftfahrzeug

Номер: DE102008045228A1

Die Erfindung betrifft einen Abgasturbolader (1) für ein Kraftfahrzeug, mit einem, ein Turbinenrad umgehenden Bypass, welcher durch ein, von einer Stelleinrichtung (2) steuer-/regelbares Wastegateventil regulierbar ist. Erfindungswesentlich ist dabei, - dass ein zweiteiliges Verbindungselement (3) vorgesehen ist, das über einen ersten Anbindungsbereich (5) lösbar fest mit der Stelleinrichtung (2) und über einen zweiten Anbindungsbereich fest mit einem Stellhebel (4) des Wastegateventils verbunden ist, und - dass im Bereich des Verbindungselementes (3) eine Einstelleinrichtung (7) vorgesehen ist, über die ein Abstand zwischen den beiden Anbindungsbereichen (5, 6) einstell- und fixierbar ist.

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14-01-2010 дата публикации

Exhaust-gas turbocharger for motor vehicle, has fast fixing device i.e. clamping sleeve, provided in area of connection elements and/or connection points for adjusting and fixing distance between connection points

Номер: DE102008032926A1

The turbocharger has a bypass that is controlled by a waste gate valve which is controllable and/or regulatable by an adjusting device. Linear two-piece connection elements (2) are connected with an adjusting device and the waste gate valve via respective connection points. A fast fixing device (1) i.e. clamping sleeve, is provided in an area of the connection elements and/or the connection points for adjusting and fixing the distance between the connection points. Parts (3, 4) of connection elements are clamped with one another in a common overlapping area by the fixing device.

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28-06-2018 дата публикации

배기가스 터보차저

Номер: KR101858169B1
Принадлежит: 보르그워너 인코퍼레이티드

본 발명은 배기가스 터보차저(1)에 관한 것으로, 배기가스 터보차저(1)는 압축기 하우징(3)을 구비한 압축기(2); 터빈 하우징(5)을 구비한 터빈(4); 압축기 하우징(3)과 터빈 하우징(5) 사이의 베어링 하우징(6); 및 하우징(8)을 구비한 제어 캡슐(7)로서, 제어 캡슐(6)을 압축기 하우징(3), 터빈 하우징(5), 또는 베어링 하우징(6)에 고정하기 위해 터보차저 상에서 체결 장치(10)와 상호작용하는 유지 장치(9)가 하우징(8)에 구비된 제어 캡슐(7)을 포함하고, 유지 장치(9)는 제어 캡슐(7)의 외주 영역(11)에 배치되고, 체결 장치(10)는 유지 장치(9)를 불완전 잠금 방식으로 고정한다.

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25-10-2007 дата публикации

Turbo-supercharger for handling exhaust gas has a turbine casing with a cleaning device for altering the amount of exhaust gas flowing through a turbine

Номер: DE102007018618A1
Принадлежит: Borg Warner Automotive Inc, BorgWarner Inc

A cleaning device alters the amount of exhaust gas that flows through a turbine. A control unit (4) links via a control rod (5) to a guide piece (6) with an active connection to the control rod. An interposed lever (7) links to a control device so as to operate it. An independent claim is also included for a tuned mass damper for a turbo-supercharger.

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12-01-1983 дата публикации

タ−ビン制御装置

Номер: JPS585410A
Принадлежит: Tokyo Shibaura Electric Co Ltd, Toshiba Corp

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

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15-06-2016 дата публикации

System for adjusting the amount of air in a gas turbine with a temperaturaktivierbaren valve.

Номер: CH702540B1
Принадлежит: Gen Electric

Es ist ein System zur Einstellung der Menge an Luft, die durch eine Druckgrenze in einer Gasturbine hindurch geliefert wird, offenbart, das einen an der Druckgrenze angeordneten Durchgang (30) enthält. Ferner ist in dem Durchgang (30) ein temperaturaktivierbares Ventil (32) montiert, das konfiguriert ist, um bei einem vorbestimmten Temperaturschwellenwert auszulösen. Insbesondere löst das temperaturaktivierbare Ventil (32) aus, um von einer Schliessstellung zu einer Offenstellung umzuschalten, wenn die lokale Temperatur an dem temperaturaktivierbaren Ventil (32) den vorbestimmten Temperaturschwellenwert erreicht oder überschreitet, um Luft zu ermöglichen, durch den Durchgang zu strömen. It is a system for adjusting the amount of air delivered through a pressure boundary in a gas turbine disclosed having a passage (30) disposed at the pressure boundary. Further, mounted in the passageway (30) is a temperature activatable valve (32) configured to initiate at a predetermined temperature threshold. In particular, the temperature-activatable valve (32) triggers to switch from a closed position to an open position when the local temperature at the temperature-activatable valve (32) reaches or exceeds the predetermined temperature threshold to allow air to flow through the passage.

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06-01-1987 дата публикации

Construction of variable stator blade of axial compressor

Номер: JPS62696A
Принадлежит: Toshiba Corp

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

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20-12-2013 дата публикации

System to control equipment of gas turbine engine with variable geometry, in particular, by means of control levers

Номер: RU2501957C2
Принадлежит: Снекма

FIELD: engines and pumps. SUBSTANCE: system to control at least two types of equipment with variable geometry, used in a gas turbine engine, besides, this gas turbine engine comprises at least one first body and one second body, and the first type of such equipment represents a stage of stator blades with variable angle of installation in a compressor of the first body, which varies between the closed position in the mode of low gas and the open position in the mode of high power, and the second type of equipment represents at least one valve of air bleed from a compressor of the second body, the condition of which varies between its opened position in the mode of low gas and its closed position in the mode of high power. A driving mechanism drives the second type of equipment by means of a part of actuation, which is actuated in a certain part of travel of the driving mechanism and is in the idle condition at the stop on the remaining part of this travel, and by means of a sliding connecting organ, implementing its idle run by actuation of the specified second equipment. EFFECT: optimised system of equipment control with variable geometry of a gas turbine engine. 10 cl, 6 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 501 957 (13) C2 (51) МПК F01D 17/20 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011117540/06, 29.09.2009 (24) Дата начала отсчета срока действия патента: 29.09.2009 (72) Автор(ы): КОЛОТТ Батист Бенуа (FR), ГОЛЛИ Брюно Робер (FR) (73) Патентообладатель(и): СНЕКМА (FR) R U Приоритет(ы): (30) Конвенционный приоритет: 30.09.2008 FR 0856565 (43) Дата публикации заявки: 10.11.2012 Бюл. № 31 2 5 0 1 9 5 7 (45) Опубликовано: 20.12.2013 Бюл. № 35 2 5 0 1 9 5 7 R U (85) Дата начала рассмотрения заявки PCT на национальной фазе: 03.05.2011 C 2 C 2 (56) Список документов, цитированных в отчете о поиске: DE 1224563 В, 08.09.1966. FR 2445439 А, 25.07.1980. ЕР 1724472 А, 22.11.2006. ЕР 1398464 А, 17.03 ...

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11-09-2013 дата публикации

Adjustment device and an exhaust gas turbocharger

Номер: KR20130100773A
Принадлежит: 로베르트 보쉬 게엠베하

본 발명은 구동 장치에 결합된, 조정 장치(1)의 구동축(7)에 총 토크를 제공하기 위한 조정 장치(1), 특히 단면 조정 부재의 조정 장치에 관한 것이다. 이런 경우 회전될 수 없게 구동축(7)과 연결된 캠 디스크(12)가 제공되어 있으며, 적어도 영역별로 원형과 다른 캠 디스크 에지(13)는 구동 장치의 구동 토크를 보조하는 보조 토크를 구동축(7)에서 발생시키기 위해 캠 디스크(12)의 회전각 위치에 따른 힘을 하나 이상의 원주 위치에서 제공받으며, 이때 구동 토크 및 보조 토크는 함께 총 토크를 형성한다. 또한, 본 발명은 배기 가스 터보차저에 관한 것이다.

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20-03-2014 дата публикации

Adjustment device of guide blades of axial compressor, system of rotating guide blades of axial compressor, and control method of guide blades of axial compressor

Номер: RU2509897C2

FIELD: machine building. SUBSTANCE: adjustment device of guide blades includes a set of rows of rotating guide blades, a set of levers, a set of adjustment knees and an adjustment drive. Levers are located on the outer side of a load-carrying element of guide blades for rotation of the latter. Each of the adjustment rings is located coaxially to the load-carrying element of guide blades and connected to the first end of one of the levers. The adjustment drive has a possibility of moving adjustment rings in a peripheral direction. One of the levers includes a spring and has the possibility of unbalanced longitudinal movement of its first end. The other invention of the group refers to a system of rotating guide blades of the axial compressor containing rotating guide blades and the above adjustment device. In one more invention of the group, at control of the guide blades of the axial compressor in the above adjustment device the lever containing a spring performs unbalanced longitudinal movement of its first end. EFFECT: inventions allow simplifying an adjustment device of guide blades of an axial compressor. 17 cl, 17 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 509 897 (13) C2 (51) МПК F01D 17/16 F04D 29/56 (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011115088/06, 15.09.2009 (24) Дата начала отсчета срока действия патента: 15.09.2009 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (43) Дата публикации заявки: 27.10.2012 Бюл. № 30 2 5 0 9 8 9 7 (45) Опубликовано: 20.03.2014 Бюл. № 8 (56) Список документов, цитированных в отчете о поиске: US 3779665 A, 18.12.1973. EP 1489267 A1, 22.12.2004. US 4295784 A, 20.10.1981. EP 1207271 A2, 22.05.2002. SU 121094 A1, 26.03.1957. RU 2145391 C1, 10.02.2000. 2 5 0 9 8 9 7 R U (86) Заявка PCT: EP 2009/061953 (15.09.2009) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 18.04.2011 (87) Публикация заявки РСТ: WO 2010/031768 ( ...

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25-04-2012 дата публикации

Power generator

Номер: JP4922110B2
Принадлежит: Kobe Steel Ltd

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14-08-2020 дата публикации

Fast closing and adjusting integrated valve for main valve of steam turbine

Номер: CN111535877A

本发明公开了一种用于汽轮机主汽门的速关调节一体阀,包括阀壳、设置在阀壳上的蒸汽进口、蒸汽出口、排汽口和操作端、安装在阀壳内部的速关阀芯、速关阀杆、活塞、活塞环、活塞衬套、螺母和节流螺塞、安装在蒸汽进口处的进汽法兰、安装在蒸汽出口处的第一端盖、安装在排汽口处的第二端盖、安装在操作端处的第三端盖以及安装在第三端盖处的位置指示器、手轮轴和手轮,所述蒸汽出口处设有调节阀杆、调节阀芯和配合调节阀芯的调节套筒。本发明将原速关阀及调节阀整合为一体式,用于主蒸汽管路与汽轮机之间的主要关闭及控制机构,并能调节汽轮机的进汽量,在紧急状态时能立即隔断汽轮机的进汽,使机组快速停机,确保使用稳定性和安全性。

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09-05-1985 дата публикации

Vane-angle controller for fluid machinery equipped with movable vane

Номер: JPS6081401A
Принадлежит: Ebara Corp

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

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03-06-2020 дата публикации

Adaptive digital turbine control system

Номер: RU2722680C1

FIELD: power engineering.SUBSTANCE: invention relates to power engineering and can be used in production, reconstruction and operation of turbine control systems. Purpose of the invention is to improve quality and flexibility of control, as well as efficiency and degree of turbine automation. Said target is achieved by using adaptive digital control system of turbine, consisting of control elements (PO), individual drives of RO, connected by feedback to position controllers of RO, and electric part, including position regulators PO and element-shaper of common control action of automatic control system (ACS), output of which is connected to inputs of position regulators of RO through corresponding setters of working medium flow rates through RO and elements-calculators, which define value of opening of RO as per CAP flow characteristics of flow-through characteristics and flow part of turbine.EFFECT: technical result of disclosed invention is to eliminate shortcomings of existing solutions, namely: higher quality of transient control processes, high quality of turbine participation in primary control of network frequency, maintaining unchanged degree of unevenness in case one or several control elements are removed from operation, simplification of the start-up and commissioning of ATS and maintenance thereof.5 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 722 680 C1 (51) МПК F01D 17/00 (2006.01) F01D 17/20 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 17/00 (2019.08); F01D 17/20 (2019.08) (21)(22) Заявка: 2019128319, 09.09.2019 (24) Дата начала отсчета срока действия патента: (73) Патентообладатель(и): Акционерное общество "Уральский турбинный завод" (RU) Дата регистрации: 03.06.2020 (45) Опубликовано: 03.06.2020 Бюл. № 16 2 7 2 2 6 8 0 R U (54) Адаптивная цифровая система регулирования турбины (57) Реферат: Изобретение относится к энергетике и может положения РО через соответствующие задатчики ...

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24-09-2019 дата публикации

A kind of regulating mechanism with displacement coordination ability

Номер: CN109372592B
Принадлежит: AECC Shenyang Engine Research Institute

本申请属于航空发动机结构设计领域,特别涉及一种具有位移协调能力的调节机构。调节机构包括:联动环(1)、弧形连接段(4)、以及内摇臂(7)。所述联动环(1)上可拆卸连接有弧形搭接段(8),所述搭接段(8)上开设有螺纹孔;所述弧形连接段(4)开设有与所述搭接段(8)上的螺纹孔相适配的安装孔,所述弧形连接段(4)通过连杆(2)与所述搭接段(8)连接,所述弧形连接段(4)上设置有连接部;所述内摇臂(7)的一端通过拉杆(3)与所述弧形连接段(4)的连接部连接,另一端通过传动杆(5)与外摇臂(6)连接。本申请可以实现外涵机匣与内涵机匣热变形差的协调,同时又不影响各元件传动关系,实现低压涡轮变几何功能。

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12-10-2017 дата публикации

Adjustable inlet guide vane assembly of gas turbine engine compressor

Номер: RU2633496C2

FIELD: engine devices and pumps. SUBSTANCE: adjustable inlet guide vane of the gas turbine engine compressor consists of an outer body, an inner ring and guide vanes arranged between them consisting of fixed posts and rotary flaps. The outer body is made of separate segments equal to the number of fixed posts. The inner surface segments of the outer body form a flow section. The inner ring has profiled grooves and holes for the flaps. The fixed posts and flaps are mounted for turning by means of cylindrical trunnions in holes of the outer body and inner ring. The segments of the outer body have flanges with mating surfaces bent along the posts profile and slots for fixed posts. The fixed posts have holes for bolt joint on the upper part of the profile and are installed in grooves of the outer body segments and into the profile grooves of the inner ring and fixed by bolt connection through holes in the flanges of the outer base segments and glue joint in the inner ring slots. In the inner ring, the posts can be fixed with plate locks. The upper trunnions of the rotary flaps are mounted in bushes of clamps secured by bolt or rivet connection on the flanges of the outer body adjacent segments. EFFECT: reduced weight reduction and simplified design of the inlet guide vane of the gas turbine engine compressor. 3 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 633 496 C2 (51) МПК F01D 17/16 (2006.01) F04D 29/56 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2015130991, 24.07.2015 (24) Дата начала отсчета срока действия патента: 24.07.2015 Дата регистрации: Приоритет(ы): (22) Дата подачи заявки: 24.07.2015 (43) Дата публикации заявки: 27.01.2017 Бюл. № 3 2 6 3 3 4 9 6 R U (56) Список документов, цитированных в отчете о поиске: RU 2013118071 A, 27.10.2014. FR 2989414 A1, 18.10.2013. RU 45462 U1, 10.05.2005. EP 1219785 A1, 03.07.2002. US 2010150708 A1, 17.06.2010. (54) РЕГУЛИРУЕМЫЙ ВХОДНОЙ НАПРАВЛЯЮЩИЙ ...

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04-10-2012 дата публикации

Integrated inlet guide vane assembly structure for a compressor

Номер: KR101187889B1
Автор: 인배석, 전광준
Принадлежит: 삼성테크윈 주식회사

본 발명은 압축기용 일체형 흡입 가이드 베인 어셈블리 구조에 있어서, 조립비 및 부품비를 절감하며, 분해 및 조립을 편리하게 할 뿐만 아니라, 흡입 공기가 베인에서 임펠러의 인듀스부로 유입되는 과정에서 베인에서 발생한 유체의 모멘텀이 감쇠되는 것을 최소화시키고, 정확한 IGV 베인 콘트롤을 가능하게 하기 위하여, 일체형 베인 콘트롤 링을 구비하며, IGV 어셈블리 케이싱의 일단은 스크롤 케이스와 주조법에 의해 일체로 형성되어 있으며 케이싱의 타단은 흡입부와 클램프 방식으로 결합되어 있는 압축기용 일체형 흡입 가이드 베인 어셈블리 구조를 제공한다. The present invention is an integrated suction guide vane assembly structure for a compressor, to reduce the assembly cost and parts costs, to facilitate the disassembly and assembly, as well as the intake of the fluid generated in the vane during the intake air flow into the inductor of the impeller In order to minimize the damping of the momentum and to enable accurate IGV vane control, an integrated vane control ring is provided, one end of the IGV assembly casing is integrally formed by the scroll case and the casting method, and the other end of the casing is Provided is an integrated suction guide vane assembly structure for a compressor that is coupled in a clamped manner.

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15-02-2018 дата публикации

Variable-capacity supercharger

Номер: WO2018029985A1
Автор: 克憲 林
Принадлежит: 株式会社Ihi

This variable-capacity supercharger is provided with a variable-capacity mechanism having a nozzle vane, an actuator (rod member 66a) that drives the nozzle vane, an operating member 70 that operates upon receiving power from the actuator, a holding part 72 provided to either one of the operating member 70 and a housing (bearing housing 2), a contact member 71 held by the holding part 72, and two parts to be contacted (protrusions 70e, 70f) that are provided to the other of the operating member 70 and the housing and that face the contact member 71 from both sides in the operating direction of the operating member 70.

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01-03-2022 дата публикации

Repair tool for turbomachinery and related method

Номер: US11260477B2
Принадлежит: MTU Aero Engines AG

A guide system for repairing turbomachinery includes a housing; a guide tube have a hollow interior for accepting a working tool module; an axial motor for moving the guide tube axially with respect to the housing; a rotational motor for rotating the guide tube with respect to the housing; and an attachment for securing the housing with respect to a turbomachinery casing. A repair kit and method are also provided.

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02-08-2016 дата публикации

Method and system for steering an insertion tube of a video inspection device

Номер: US9404871B2
Принадлежит: General Electric Co

A method and system for steering an insertion tube of a video inspection device is disclosed for detecting a precise steering request made by displacing a pointing device from its stationary position and then returning the pointing device to or near its stationary position within a short interval of time. This precise steering request is then used by the video inspection device to steer the insertion tube a fixed distance in a direction based on the direction of the displacement of the pointing device for precise positioning of the camera head of the insertion tube.

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16-04-2021 дата публикации

Axial Fan Blade Tip Clearance Control Device and Method of Controlling Axial Fan Blade Tip Clearance Using The Same

Номер: KR102241290B1
Принадлежит: 한국과학기술연구원

Provided are an axial-flow fan blade clearance control apparatus and an axial-flow fan blade clearance control method using the same. The axial-flow fan blade clearance control apparatus includes: a housing installed to house a rotor, formed to be movable in one direction, and including a gear part on the outer circumference; a driving gear provided to be interlocked with the gear part to enable the housing to be moved relatively in one direction by providing a rotation force to the housing; and an optical sensor installed in the housing to measure the clearance between the housing and the rotor. A slope part inclined in one direction is provided on the inner circumference of the housing spaced apart from the rotor, and the housing is moved in one direction based on the clearance, thereby controlling the distance between the slope part and a blade of the rotor.

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23-01-1985 дата публикации

Adjustable guiding apparatus

Номер: EP0131719A2

Die Erfindung bezieht sich auf einen verstellbaren Leitapparat einer Strömungsmaschine, insbesondere einer Abgasturbine eines Turboladers, mit einem Kranz von konzentrisch um eine Rotorachse (12) angeordneten Leitschaufeln, die zwischen Endbegrenzungen um Schwenkachsen (10) schwenkbar sind. Die Schwenkachsen (10) sind im vorderen, den Anströmkanten zugeordneten Bereich der Leitschaufeln (6) angeordnet, wobei mittels eines Verstellringes (14) oder dergleichen eine der genannten Endbegrenzungen einstellbar ist. Spalt- und/oder Stoßverluste ergeben sich entsprechend der jeweiligen Einstellung der Leitschaufeln. Es soll die Aufgabe gelöst werden, einen Leitapparat mit geringem konstruktiven Aufwand vorzuschlagen, bei welchem Spalt- und/oder Stoßverluste reduziert werden. Zur Lösung wird vorgeschlagen, daß die Leitschaufeln (6) derart angeordnet sind, daß sie unter den Strömungskräften in einem mittels der Endbegrenzungen vorgegebenen Einstellwinkelbereich frei schwenkbar sind. Die Leitschaufeln (6) sind bei geringer Belastung in dem vorgegebenen Einstellwinkelbereich frei schwenkbar und bei zunehmender Belastung liegen die Leitschaufeln (6) an der einstellbaren Endbegrenzung an. The invention relates to an adjustable diffuser of a turbomachine, in particular an exhaust gas turbine of a turbocharger, with a ring of guide vanes which are arranged concentrically around a rotor axis (12) and can be pivoted between end limits about pivot axes (10). The pivot axes (10) are arranged in the front area of the guide vanes (6) assigned to the leading edges, one of the end limits mentioned being adjustable by means of an adjusting ring (14) or the like. Gap and / or impact losses result in accordance with the respective setting of the guide vanes. The object of the invention is to propose a guide apparatus with little design effort, in which gap and / or impact losses are reduced. As a solution, it is proposed that the guide vanes (6) be arranged in such a way that they can be ...

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10-09-2009 дата публикации

Turbocharger with an actuator for opening and closing a wastegate duct

Номер: DE102008011416A1
Принадлежит: Continental Automotive GmbH

Die Erfindung betrifft einen Turbolader mit einem Wastegate-Kanal, wobei der Wastegate-Kanal über eine Betätigungseinrichtung geöffnet und geschlossen werden kann, wobei die Betätigungseinrichtung ein Schließelement aufweist, dass in den Wastegate-Kanal einschwenkbar ist, um diesen zu schließen. The invention relates to a turbocharger with a wastegate channel, wherein the wastegate channel can be opened and closed via an actuating device, wherein the actuating device has a closing element that can be pivoted into the wastegate channel in order to close it.

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08-07-2015 дата публикации

Control device for a valve flap

Номер: EP2317095B1
Автор: Michael Baeuerle
Принадлежит: ROBERT BOSCH GMBH

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