ТРУБЧАТАЯ КАМЕРА СГОРАНИЯ ДЛЯ КОНСТРУКЦИИ ТРУБЧАТО-КОЛЬЦЕВОЙ КАМЕРЫ СГОРАНИЯ В ГАЗОВОЙ ТУРБИНЕ

Трубчатая камера сгорания для конструкции трубчато-кольцевой камеры сгорания в газовой турбине, по меньшей мере, содержит, по существу, цилиндрический кожух с расположенной в осевом направлении выше по потоку передней панелью и расположенным в осевом направлении ниже по потоку выпускным концом, несколько горелок с предварительным смешением, проходящих в направлении выше по потоку от упомянутой передней панели и имеющих выход горелки, поддерживаемый посредством этой передней панели, для подачи топливо-воздушной смеси в зону сгорания внутри кожуха. До четырех горелок с предварительным смешением прикреплены к передней панели, по существу, в кольцевом расположении. Каждая горелка имеет смесительную трубку для возбуждения вихревого потока упомянутой топливо-воздушной смеси. Центральная горелка не предоставлена. Каждая горелка имеет конический вихревой генератор. Выравнивание центральной продольной оси, по меньшей мере, одной горелки с предварительным смешением, прикрепленной к передней панели ...

УСТРОЙСТВО И СПОСОБ УПРАВЛЕНИЯ УСТАНОВКОЙ ВНУТРЕННЕГО СГОРАНИЯ С ПОВЫШЕНИЕМ ДАВЛЕНИЯ

Изобретение относится к энергетике. Способ управления работой установки внутреннего сгорания с повышением давления, включающий: нахождение скважности импульсов топливной форсунки и частоты циклов сгорания, которые соответствуют заданной рабочей точке нагрузки и заданному коэффициенту заполнения камеры сгорания установки; определение уставки давления подачи топлива, уставки момента впрыска для топливной форсунки и уставки момента зажигания, которые обеспечивают найденную скважность импульсов топливной форсунки и найденную частоту циклов сгорания; и передачу управляющего сигнала давления подачи топлива, содержащего уставку давления подачи топлива, в устройство обеспечения давления топлива, управляющего сигнала топливной форсунки, содержащего уставку момента впрыска топлива, в топливную форсунку и управляющего сигнала момента зажигания, содержащего уставку момента зажигания, в узел зажигания установки. Также представлены установка внутреннего сгорания с повышением давления и контроллер для ...

СПОСОБ И УСТРОЙСТВО ДЛЯ ПОДАЧИ ТОПЛИВА В ГАЗОВУЮ ТУРБИНУ

Изобретения относятся к способу и устройству для подачи топлива в газовую турбину. Описан способ управления подачей топлива в камеру сгорания газовой турбины,содержащей компрессор выше по потоку относительно камеры сгорания, причем способ содержит: подачу топлива в камеру сгорания; получение входного давления воздуха на входе компрессора; получение входной температуры воздуха на входе компрессора; получение выходного давления воздуха на выходе компрессора; получение сигнала отбора воздуха, указывающего количество воздуха, не поступающего в камеру сгорания; оценивание тепловыделение топлива, подаваемого в камеру сгорания, на основе входного давления воздуха, входной температуры воздуха, выходного давления воздуха и сигнала отбора воздуха; сравнение оцененного тепловыделения с требуемым тепловыделением, чтобы получить сигнал ошибки; и управление топливным клапаном, регулирующим подачу топлива в камеру сгорания, на основе сигнала ошибки. Технический результат изобретений – повышение стабильности ...

ГАЗОТУРБИННАЯ СИСТЕМА, СПОСОБ ИЗМЕНЕНИЯ ВЫХОДНОЙ МОЩНОСТИ ГАЗОТУРБИННОЙ СИСТЕМЫ, СПОСОБ РАСШИРЕНИЯ ДИАПАЗОНА РЕГУЛИРОВАНИЯ ГАЗОТУРБИННОЙ СИСТЕМЫ, СПОСОБ И СИСТЕМА ДЛЯ ПОВЫШЕНИЯ ЭФФЕКТИВНОСТИ ГАЗОВОЙ ТУРБИНЫ

Газотурбинная система содержит подсистему защиты компрессора, подсистему спящего режима и подсистему управления, которая управляет подсистемой компрессора и подсистемой спящего режима. При частичных нагрузках на турбинную систему подсистема защиты компрессора поддерживает воздушный поток через компрессор с коэффициентом расхода воздушного потока для частичной нагрузки выше минимального коэффициента расхода, когда в компрессоре возникают аэромеханические напряжения. Поддерживается соотношение компонентов топливовоздушной смеси, при котором компоненты выбросов выхлопных газов из турбины сохраняются ниже заранее заданного уровня выбросов компонента при работе на частичных нагрузках. Технический результат – повышение эффективности в управлении газовой турбиной на низких уровнях нагрузки. 5 н. и 32 з.п. ф-лы, 12 ил.

ТЕСТ НА ОТСУТСТВИЕ ГАШЕНИЯ КАМЕРЫ СГОРАНИЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Способ наземного контроля нормальной работы установленного на самолете авиационного газотурбинного двигателя. Для этого производят испытание, которое содержит осуществление - на работающем газотурбинном двигателе и начиная от определенного режима - быстрого уменьшения расхода топлива по запрограммированному понижению с целью оценки стойкости к самогашению камеры сгорания упомянутого газотурбинного двигателя во время быстрого сброса его оборотов в полете. Технический результат - повышение надежности диагностики газотурбинного двигателя. 5 н. и 3 з.п. ф-лы, 1 ил.

СПОСОБ РАБОТЫ СЖИГАЮЩЕГО УСТРОЙСТВА ГАЗОВОЙ ТУРБИНЫ И СЖИГАЮЩЕЕ УСТРОЙСТВО ДЛЯ ГАЗОВОЙ ТУРБИНЫ

Способ работы сжигающего устройства для газовой турбины, содержащего по меньшей мере первую камеру сгорания, отклоняющий узел и последовательную камеру сгорания. В первой камере сгорания предварительно смешанную топливовоздушную смесь сжигают в устойчивом пламени при средней температуре пламени, составляющей от 1550 К до 1800 К. На нижнем по потоку конце первой камеры сгорания и выше по потоку от отклоняющего узла массовый поток дополнительного воздуха впрыскивают в поток горячих газов для того, чтобы понизить температуру ниже 1400 К. Затем смесь горячих газов и дополнительного воздуха вводят в отклоняющий узел и отклоняют в нем, по меньшей мере, в окружном направлении. Массовый поток дополнительного топлива впрыскивают ниже по потоку от местоположения указанного впрыскивания воздуха, образуя смесь горячих газов, воздуха и топлива с временем самовоспламенения от 1 мс до 10 мс. Смесь горячих газов, воздуха и топлива сжигают в последовательной камере сгорания посредством самовоспламенения ...

СПОСОБ ЭКСПЛУАТАЦИИ КАМЕРЫ СГОРАНИЯ ПРИ РАБОТЕ В НЕУСТАНОВИВШЕМСЯ РЕЖИМЕ

Изобретение относится к способу эксплуатации камеры сгорания при работе в неустановившемся режиме. В камеру сгорания подают, по меньшей мере, топливо. Неустановившийся режим включает в себя период, имеющий продолжительность, в течение которого топливо подают в количестве меньшем, чем критическое количество топлива. Способ включает в себя задание предельного значения для длительности периода и регулирование подачи топлива так, чтобы длительность периода была меньше или равна предельному значению. Изобретение позволяет нейтрализовать пульсации горения, возникающие во время работы в неустановившемся режиме. 8 з.п. ф-лы, 7 ил.

СПОСОБ И УСТРОЙСТВО ДЛЯ ОКИСЛЕНИЯ ТОПЛИВА

Изобретение относится к энергетике. Способ окисления топлива включает в себя несколько этапов. В первом рабочем режиме смесь, содержащая топливо, поступившее из источника топлива, сжимается в компрессоре системы окисления топлива; сжатое топливо окисляется в реакционной камере системы окисления топлива; и окисленное топливо расширяется для генерирования кинетической энергии вращения. Во втором рабочем режиме топливо из источника топлива подается в обход компрессора, и топливо, которое прошло в обход компрессора, окисляется в реакционной камере. Также представлено устройство для осуществления способа. Изобретение позволяет принимать топливо из источника топлива и подавать топливо, принятое из источника топлива, в реакционную камеру, или во впуск компрессора для воздушно-топливной смеси, или путем подачи топлива в обход компрессора через теплообменник, нагреваемый потоком газов, выходящих из реакционной камеры. 2 н. и 17 з.п. ф-лы, 4 ил.

СЖИГАЮЩЕЕ УСТРОЙСТВО ГАЗОТУРБИННОЙ УСТАНОВКИ

Изобретение относится к сжигающему устройству газотурбинной установки. Сжигающее устройство газотурбинной установки содержит пилотную горелку, пилотный клапан регулирования подачи топлива, который регулирует расход топлива, подаваемого в пилотную горелку, основную горелку для горения предварительно приготовленной смеси, расположенную на внешней периферийной стороне пилотной горелки, множество основных клапанов регулирования подачи топлива, которые регулируют расходы топлива, индивидуальным образом подаваемого во множество секторов горелки, на которые разделена основная горелка в окружном направлении, и контроллер, выполненный с возможностью управления пилотным клапаном регулирования подачи топлива и множеством основных клапанов регулирования подачи топлива, при этом контроллер выполнен с возможностью управления множеством основных клапанов регулирования подачи топлива таким образом, что, когда топливо подлежит подаче во все из множества секторов горелки, возникает различие в расходе топлива ...

ДОЗАТОР ТОПЛИВА ДЛЯ ГАЗОТУРБИННОЙ УСТАНОВКИ

Изобретение относится к области управления газотурбинными двигателями, а именно к устройствам управления подачей газообразного топлива в камеру сгорания наземной газотурбинной установки. Задачей, на решение которой направлено заявляемое изобретение, является повышение надежности и точности дозирования топлива. Решается задача с помощью дозатора топлива, содержащего корпус, дозирующий элемент со штоком и электродвигатель, соединенный с этим штоком. Дозатор топлива содержит также датчик положения дозирующего элемента и блок управления электродвигателем, соединенный с датчиком положения и с системой управления газотурбинной установкой. Причем в качестве электродвигателя используется гибридный шаговый двигатель, конструктивно объединенный с блоком управления, а в качестве датчика положения используется оптический энкодер, соединенный с валом гибридного шагового двигателя. 2 з.п. ф-лы, 2 ил.

Система подачи жидкого топлива газотурбинной установки

Изобретение относится к области энергомашиностроения, конкретно к газотурбостроению, в частности к системе подачи жидкого топлива к горелкам камеры сгорания и может быть использовано в составе двухтопливной энергетической газотурбинной установки. Система подачи жидкого топлива содержит магистраль подачи жидкого топлива 1 к горелкам камеры сгорания ГТУ, линию возврата жидкого топлива 2 от горелок камеры сгорания газовой турбины. Магистраль подачи жидкого топлива 1 содержит последовательно, друг за другом, установленный сдвоенный фильтр жидкого топлива 3, мембранные баки 7, насос жидкого топлива 4, клапан рециркуляции жидкого топлива 17, аварийный запорный клапан 5, регулирующий клапан 6. На линии возврата жидкого топлива 2 последовательно друг за другом установлены аварийный запорный клапан 8 и регулирующий клапан 9. Магистраль подачи жидкого топлива 1 связана с линией возврата жидкого топлива 2 через линию рециркуляции жидкого топлива 26, включающую регулятор сопротивления 25, которая с ...

Малоэмиссионная камера сгорания и способ подачи в ней топлива

Малоэмиссионная камера сгорания газотурбинного двигателя содержит как минимум два топливных коллектора: основной и пилотный, кран перераспределения топлива, как минимум два горелочных устройства, каждое из которых снабжено криволинейным каналом, образованным двумя спрофилированными обечайками. Внутренняя поверхность криволинейного канала сопряжена с центральным телом горелочного устройства, на котором установлен аксиальный завихритель и трубки подачи топлива в проточную часть горелочного устройства от основного топливного коллектора. На внешней поверхности криволинейного канала размещен выравнивающий коллектор для подвода топлива через соответствующие трубки из пилотного коллектора в проточную часть горелочного устройства, которое соединено с жаровой трубой, имеющей отверстия для подачи воздуха, внутри которой соосно с ней расположен экран, состоящий из поперечной кольцевой части и продольной цилиндрической части. Экран и жаровая труба образуют проточную полость для воздуха. На входе жаровой ...

МОДУЛЬНОЕ УСТРОЙСТВО ГАЗОВОЙ ТУРБИНЫ ДЛЯ ПОДАЧИ ТОПЛИВА

... 1. Газовая турбина, прежде всего силовая установка газовой турбины, с устройством подачи топлива и устройством управления, отличающаяся тем, что по меньшей мере части устройства управления, прежде всего блока управления силовой установки, интегрированы в устройство (10) подачи топлива. ! 2. Газовая турбина по п.1, отличающаяся тем, что устройство (10) подачи топлива имеет по меньшей мере один насос (12) и по меньшей мере один приводящий в действие насос(-ы) (12) электродвигатель (13), при этом по меньшей мере один насос (12) и по меньшей мере один электродвигатель (13) образуют блок (11) двигатель-насос. ! 3. Газовая турбина по п.2, отличающаяся тем, что устройство (10) подачи топлива в дополнение к блоку (11) двигатель-насос имеет по меньшей мере один блок (16) регулирования двигателя для управления или регулирования работы по меньшей мере одного электродвигателя (13) блока (11) двигатель-насос. ! 4. Газовая турбина по п.3, отличающаяся тем, что интегрированные в устройство (10) подачи ...

УСТРОЙСТВО СЛИВА ТЕКУЧИХ СРЕД ДЛЯ АВИАЦИОННОГО ДВИГАТЕЛЯ

Устройство слива текучих сред для авиационного двигателя, содержащее коллектор, выполненный с возможностью сбора текучих сред, сливаемых из двигателя, содержащее средства откачки текучих сред, содержащихся в коллекторе, и удаления этих текучих сред, и средства контроля, выполненные с возможностью оповещения о ненормальном сборе текучих сред коллектором, причем эти средства контроля выполнены с возможностью активации, когда расход собираемых текучих сред превышает пропускную способность средств откачки. Описаны также авиационный двигатель, содержащий данное устройство слива, и способ контроля такого авиационного двигателя. Технический результат изобретения – повышение эффективности слива текучих сред авиационного двигателя. 3 н. и 7 з.п. ф-лы, 10 ил.

СИСТЕМА УПРАВЛЕНИЯ АВИАЦИОННЫМ УЗЛОМ ПРИВОДА ВНУТРЕННЕГО СГОРАНИЯ С ВОСПЛАМЕНЕНИЕМ СЖАТИЯ

... 1. Способ управления для авиационного узла привода внутреннего сгорания с воспламенением от сжатия, при этом авиационный узел привода внутреннего сгорания с воспламенением от сжатия имеет элемент двигателя, элемент трансмиссии и элемент воздушного винта, причем способ управления содержит этапы, на которых:- измеряют параметр давления в каждой из множества камер сжатия элемента двигателя;- предоставляют измеряемый параметр давления в устройство системы управления;- предоставляют множество управляющих программ для устройства системы управления; ипричем устройство системы управления действует в соответствии с измеряемым параметром давления для осуществления стратегии управления в элементе двигателя.2. Способ управления по п. 1, включающий в себя этап, на котором реализуют стратегию управления в элементе двигателя посредством воздействия на работу, по меньшей мере, одного топливного инжектора.3. Способ управления по п. 2, включающий в себя этап, на котором воздействуют на распределение по времени ...

СПОСОБ ЗАПУСКА ГАЗОВОЙ ТУРБИНЫ

... 1. Способ запуска газовой турбины, содержащей, по меньшей мере, один компрессор (10), который сжимает воздух, вводимый в него через впускной канал (12), по меньшей мере, одну камеру (14) сгорания, в которой сжатый воздух смешивается и сжигается вместе с газообразным топливом, поступающим из подводящего канала (16), и, по меньшей мере, одну турбину (20), которая преобразует энергию сжигаемого газа, выходящего из камеры (14) сгорания, в работу, причем способ включает в себя этапы: ! а) установления заданной минимальной величины (FSR1) потока топлива, поступающего в камеру (14) сгорания, и осуществления первой попытки воспламенения; и ! b) постепенного увеличения величины (FSRn) потока топлива, поступающего в камеру (14) сгорания, и осуществления дальнейших попыток воспламенения до полного воспламенения воздушно-топливной смеси и последующего запуска турбины (20) или до тех пор, пока будет достигнута заданная максимальная величина (FSRmax) упомянутого потока топлива. ! 2. Способ по п.1, при ...

ГАЗОТУРБИННАЯ УСТАНОВКА И УСТАНОВКА, СОДЕРЖАЩАЯ ЛОПАТКИ-ФОРСУНКИ (ВАРИАНТЫ)

... 1. Газотурбинная установка, содержащая ! компрессор, выполненный с возможностью приема и сжатия рабочей текучей среды, ! камеру сгорания, выполненную с возможностью приема сжатой рабочей текучей среды из компрессора и топлива и с возможностью сжигания смеси сжатой рабочей текучей среды и топлива с образованием выхлопного газа, и ! турбину, имеющую первую секцию и вторую секцию и выполненную с возможностью приема выхлопного газа из камеры сгорания и использования его для вращения вала, при этом между первой и второй секциями турбины расположено кольцевое устройство сгорания для вторичного подогрева, которое содержит лопатку-форсунку для предварительного смешивания, выполненную с возможностью смешивания воздуха и топлива с созданием воздушно-топливной смеси и с возможностью введения этой смеси в выхлопной газ, поступающий из первой секции турбины. ! 2. Газотурбинная установка по п.1, в которой указанное кольцевое устройство сгорания содержит кольцевой канал, имеющий внутреннюю кольцевую стенку ...

СПОСОБ И УСТРОЙСТВО ДЛЯ МОНИТОРИНГА СИСТЕМЫ ПРИВЕДЕНИЯ В ДЕЙСТВИЕ НА ОСНОВЕ СЕРВОКЛАПАНОВ

... 1. Способ для мониторинга системы (1) приведения в действие, содержащей устройство (2) управления, сервоклапан (3) и актуатор (4), управляемый посредством сервоклапана (3), причем устройство управления может определять управляющий ток (I) согласно заданному значению (Pos_c) позиции и измеренной позиции (Pos_m) актуатора (4) и предоставлять упомянутый управляющий ток (I) в сервоклапан (3), при этом способ мониторинга отличается тем, что он содержит:- этап (E1), на котором определяют стабилизированный режим посредством проверки того, что упомянутая измеренная позиция (Pos_m) остается постоянной,- этап (E3), на котором определяют среднее значение (I) управляющего тока в ходе определения стабилизированной позиции, и- этап (E4), на котором сравнивают упомянутое среднее значение с предварительно определенным пороговым значением.2. Способ мониторинга по п. 1, содержащий, перед этапом определения (E3), этап (E2), на котором ожидают в течение периода ожидания, в ходе которого определяется стабилизированный ...

УСТРОЙСТВО ЗАЩИТЫ ОТ ЗАБРОСА ОБОРОТОВ АВИАЦИОННОГО ДВИГАТЕЛЯ

СПОСОБ УПРАВЛЕНИЯ БИСТАБИЛЬНЫМ ВЕНТИЛЕМ ВЫКЛЮЧЕНИЯ ДЛЯ АВИАЦИОННОГО ДВИГАТЕЛЯ

СИСТЕМА АВТОМАТИЧЕСКОГО ТЕСТИРОВАНИЯ ДЛЯ ГАЗОВОЙ ТУРБИНЫ

ТЕРМОУПРАВЛЯЕМЫЙ УЗЕЛ ДЛЯ ГАЗОТУРБИННОЙ СИСТЕМЫ (ВАРИАНТЫ) И СПОСОБ ПОТОКА ОХЛАЖДАЮЩЕГО ВОЗДУХА

... 1. Термоуправляемый узел для газотурбинной системы, содержащий:элемент теплопередачи, имеющий первую часть и вторую часть, при этом первая часть расположена внутри первой полости, имеющей первую температуру, а вторая часть расположена во второй полости, имеющей вторую температуру, причем элемент теплопередачи проходит через полую стенку, и первая температура больше, чем вторая температура;термочувствительный элемент, расположенный внутри второй полости и функционально связанный с элементом теплопередачи, иустройство регулирования потока, расположенное внутри второй полости и выполненное с возможностью смещения в ответ на изменение температуры в первой полости.2. Термоуправляемый узел по п.1, в котором первая полость имеет первое давление, а вторая полость имеет второе давление, при этом второе давление больше, чем первое давление.3. Термоуправляемый узел по п.2, в котором устройство регулирования потока содержит тарелку клапана и шток клапана, проходящий от тарелки клапана к термочувствительному ...

УСТРОЙСТВО ПРЕДВАРИТЕЛЬНОГО СМЕШИВАНИЯ, ТУРБИННЫЙ ДВИГАТЕЛЬ И СПОСОБ ИЗГОТОВЛЕНИЯ УСТРОЙСТВА ПРЕДВАРИТЕЛЬНОГО СМЕШИВАНИЯ

... 1. Устройство предварительного смешивания, содержащеесмесительную часть, выполненную с возможностью приема газового потока, поступающего в направлении потока, и топлива, вводимого по существу перпендикулярно направлению потока, и содержащую обод, имеющий по существу цилиндрическую форму, и завихритель, имеющий (I) центральную часть, расположенную по существу в середине цилиндрической формы вдоль направления потока, и (ii) ряд лопаток, проходящих от центральной части к ободу, причем лопатки выполнены с обеспечением вращательного движения в потоке, содержащем принятый газовый поток и введенное топливо, при прохождении этого потока через смесительную часть, и по меньшей мере некоторые лопатки имеют выходную кромку с волнистым профилем, выполненную с обеспечением создания смесительных зон внутри выходящего потока.2. Устройство по п.1, в котором соседние зубцы, образованные волнистым профилем, изогнуты в противоположных направлениях относительно плоскости лопатки.3. Устройство по п.1, в котором ...

УСТРОЙСТВО И СПОСОБ ДЛЯ СВЕДЕНИЯ К МИНИМУМУ ОБРАЗОВАНИЯ УГЛЕРОДИСТЫХ ОТЛОЖЕНИЙ В ГАЗОТУРБИННЫХ ДВИГАТЕЛЯХ

... 1. Устройство (200) для сведения к минимуму образования углеродистых отложений в газотурбинных двигателях, включающее:отсек (202) газовой турбины;топливный компонент (206), расположенный внутри отсека (202) газовой турбины, итермоэлектрический элемент (208), расположенный, по меньшей мере, частично, вокруг топливного компонента (206);причем термоэлектрический элемент (208) выполнен для обмена теплом с топливным компонентом (206);2. Устройство (200) по п.1, в котором термоэлектрический элемент (208) содержит элемент (300) Пельтье, распложенный между холодным теплоприемником (310) и горячим теплоприемником (312).3. Устройство (200) по п.2, в котором к элементу (300) Пельтье подведено напряжение для регулирования теплопереноса между холодным теплоприемником (310) и горячим теплоприемником (312).4. Устройство (200) по п.3, в котором холодный теплоприемник (310) и горячий теплоприемник (312) зависят от полярности напряжения, приложенного к элементу (300) Пельтье.5. Устройство (200) по п.2, в ...

СПОСОБ И УСТРОЙСТВО ДЛЯ РЕГУЛИРОВАНИЯ ПОРОГОВОГО ЗНАЧЕНИЯ РАСХОДА ТОПЛИВА

... 1. Способ регулирования порогового значения (С0(асс), С0(dec)) расхода топлива для использования в разомкнутом контуре для регулирования турбореактивного двигателя (1), приводящего в движение летательный аппарат, при этом способ включает:этап (Е20) получения первой оценки (Е1) расхода топлива, впрыскиваемого в камеру сгорания турбинного двигателя (1), которая вырабатывается дозатором (2) топлива турбореактивного двигателя;этап (Е30) получения второй оценки (Е2) расхода топлива, впрыскиваемого в камеру сгорания, причем вторая оценка является более точной, чем первая оценка, для по меньшей мере одного диапазона значений расхода топлива, и вырабатывается устройством (5) оценки, имеющим расходомер (5А); иэтап (Е70, Е80) регулирования порогового значения (С0(асс), С0(dec)) расхода топлива с помощью разности (ΔЕ) между первой оценкой (Е1) и второй оценкой (Е2).2. Способ регулирования по п. 1, при котором этап (Е70, Е80) регулирования включает сложение пороговому значению (С0(асс), С0(dec)) расхода ...

СПОСОБ РАБОТЫ СЖИГАЮЩЕГО УСТРОЙСТВА ГАЗОВОЙ ТУРБИНЫ И СЖИГАЮЩЕЕ УСТРОЙСТВО ДЛЯ ГАЗОВОЙ ТУРБИНЫ

... 1. Способ работы сжигающего устройства для газовой турбины, по меньшей мере содержащего (в направлении потока горячих газов) первую камеру (1) сгорания, отклоняющий узел (2), последовательную камеру (3) сгорания, при этом первая камера (1) сгорания представляет собой камеру сгорания с предварительным смешиванием с по меньшей мере одной горелкой (4) предварительного смешивания для впрыска смеси воздуха (5) и газообразного и/или жидкого топлива (6) в зону (7) горения, а последовательная камера (3) сгорания представляет собой камеру сгорания с самовоспламенением и присоединена к первому ряду (8) лопаток ротора турбины, отличающийся тем, что в первой камере (1) сгорания предварительно смешанную топливовоздушную смесь сжигают в устойчивом пламени при средней температуре пламени, составляющей от 1400 К до 1800 К, при этом на нижнем по потоку конце первой камеры (1) сгорания массовый поток дополнительного воздуха (9) впрыскивают в поток горячих газов для того, чтобы понизить температуру ниже 1400 ...

COMPOSITE SEALING ARRANGEMENT

ACCELERATION LIMITER FOR A GAS TURBINE

Pumping arrangement

System and method for controlling a gas turbine engine afterburner

APPARATUS FOR CONTROLLING THE FUEL SUPPLY TO THE AFTER-BURNER OF A BY-PASS FLOW GAS-TURBINE JET ENGINE

DEVICE FOR CONTROLLING FUEL SUPPLY TO GAS TURBINE PLANT

... 1315740 Gas turbine engines - fuel control LENINGRADSKY METALLICHESKY ZAVOD IMENI XXII SIEZDA KPSS 7 Dec 1971 56706/71 Heading FIG The invention relates to a device for controlling fuel supply to a gas turbine engine, the device comprising a valve 1 controlled by the turbine speed governor (not shown), a fuel pressure drop regulator 2 and a valve 3 controlled by the regulator 2. The valve 1 comprises two valves 4 and 5 connected in series flow, the two valve members being mounted on a common rod 6, the pressure drop across the valve 4 being communicated through lines 8 to the pressure drop transmitter 9 of the regulator 2. The transmitter 9 controls the position of a control valve 10 which in turn controls flow of pressure fluid to actuator 11 which in turn controls the position of valve 3 in the fuel line leading to the burner 12. The valve 3 is by-passed at starting by means of a member 13.

FUEL CONTROL SYSTEM

... 1316427 Fluid regulation JOSEPH LUCAS (INDUSTRIES) Ltd 11 Sept 1970 [12 June 1969] 29750/69 Heading G3H [Also in Division F1] The invention relates to a reheat fuel control system for a gas turbine jet engine (see Division Fl), control pressures being derived by means of a fluidic device as shown in Figs. 2 and 3 which comprises axially aligned nozzles 70, 71 formed with bores 72, 73, the bore 72 opening from a chamber 74. The walls of the chamber 74 are defined by arcs 75, 76 the centres of which are displaced from each other and from the axis of the nozzle. A pair of passages 77, 78 having aligned openings 79, 80 open into the chamber, the opening 79 being tangential to the arc 75 while the opening 80 is displaced from tangency to the arc 76. A further pair of passages 81, 82 having openings 83, 84 is provided at the other side of the chamber. The passages 78, 81 are commonly connected as are the passages 77, 82. When fluid-pressure in the passages 77, 82 is greater than that in passages ...

Method and apparatus for the rapid startup and rapid increase in output of a gas turbine plant

Method and system to facilitate over-speed protection

An over-speed protection system 40 for use with a gas turbine engine 10 includes a first fuel system interface 56, a second fuel system interface 58, a first driver control system 102 coupled in communication to the first fuel system interface and the second fuel system interface, the first driver control system including a first driver 106 and a second driver 108 that is different than the first driver, and a second driver control system 104 coupled in communication to the first fuel system interface and the second fuel system interface, the second driver control system including the first driver 110 and the second driver 112. The drivers may comprise solenoid current drivers or torque motor current drivers. The driver control systems may receive a speed signal from a speed sensor configured to sense the rotational speed of the rotor of the gas turbine engine.

Method and apparatus for controlling the operation of a gas turbine

Systems and methdods for closed loop emissions control

Method for managing the operation of a fuel metering unit

Gas fuel turbine engine for reduced oscillations

Method and apparatus for controlling the operation of a gas turbine

Shut-off valve arrangements for fluids

A servo-operated shut-off valve arrangement has a main valve responsive to a servo pressure and fluid pressure operated pilot valve for controlling the servo pressure. The pilot valve has two stable operating positions in which the main valve servo pressure is respectively vented and maintained. The fluid pressure which operates the pilot valve is controlled by a valve device movable in opposite directions from a center-stable position to effect movement of the pilot valve. The pilot valve co-operates with the center-stable valve device so that the pilot valve remains in the position in which it was last urged by movement of the valve device away from its stable central position.

TURBINE PLANT FUEL CONTROL

Improving deceleration of a gas turbine

A gas turbine engine for an aircraft comprises a high-pressure (HP) spool, HP compressor (105, figure 1), first electric machine (117) driven by an HP turbine (107); low-pressure (LP) spool, LP compressor (104), second electric machine (119) driven by an LP turbine (108), and an engine controller (123) configured to, in response to a change of a power lever angle setting indicative of an deceleration event, reduce fuel flow to a combustion system by a fuel metering unit, and operate the first electric machine in a generator mode to reduce the HP spool rotational speed and engine core mass flow. The controller may operate the second electric machine in a generator mode to further reduce engine mass flow. Electrical power may be supplied to an anti-icing system 304, battery 305, or capacitor. A method comprising identifying a condition to the effect that current fuel-air ratio in combustor is indicative of weak extinction onset, and extracting mechanical shaft power from HP spool to prevent ...

REGULATION DEVICE AND ENGINE WITH THIS DEVICE

PROCEDURE, DEVICES AND/OR SYSTEMS REGARDING FUEL DELIVERY SYSTEMS FOR INDUSTRIAL MACHINES

GEGENSTROMBRENNKAMMER FOR GAS TURBINES

Integrated engine control system for a gas turbine engine

Aero compression combustion drive assembly control system

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engiune member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included.

Systems and methods to respond to grid overfrequency events for a stoichiometric exhaust recirculation gas turbine

A method includes combusting a fuel and an oxidant in a combustor of an exhaust gas recirculation (EGR) gas turbine system that produces electrical power and provides a portion of the electrical power to an electrical grid. The method further includes controlling, via one or more processors, one or more parameters of the EGR gas turbine system to decrease the portion of the electrical power provided to the electrical grid in response to an over-frequency event associated with the electrical grid, wherein controlling the one or more parameters comprises decreasing a flow rate of fuel to the combustor in response to the over-frequency event.

A METHOD AND A DEVICE FOR SUPPLYING FUEL TO A COMBUSTION CHAMBER

The invention relates to a method and a device (1) for supplying fuel to a combustion chamber which comprises at least one main injector (3) and at least one pilot injector (2). The device comprises a fuel tank (4), a line system (5) coupled from the fuel tank to the injectors (2, 3), a pump (6) for pumping fuel from the tank to the injectors, and a first regulator valve (7) for regulating the flow of fuel in a first line (8) in the system whichis connected to said pilot injector (2). The device further comprises a second regulator valve (9) for regulating the flow of fuel through a second line (10) in the system, which is connected to said pilot injector (2). The second regulator valve (9) is designed to regulate a substantially smaller flow than the first regulator valve (7).

IMPROVED START FLOW MEASUREMENT

A method and apparatus for measuring a start fuel flow to a pilot nozzle (34) of a fuel system (28) of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles (34, 37).

NON-FLAME-OUT TEST FOR THE COMBUSTION CHAMBER OF A TURBINE ENGINE

Procédé de contrôle au sol du bon fonctionnement d'une turbomachine aéronautique avionnée. Pour cela l'essai consiste, sur la turbomachine en fonctionnement et à partir d'un régime déterminé, en la réalisation d'une réduction rapide du débit de carburant selon une décroissance programmée, dans le but d'évaluer la résistance à l'extinction de la chambre de combustion de ladite turbomachine lors d'une manuvre de décélération rapide de son régime en vol.

GAS TURBINE PLANT CONTROL SYSTEM

SINGLE-SHAFT COMBINED PLANT

GAS TURBINE POWER PLANT CONTROL APPARATUS HAVING IMPROVED MONITORING AND ALARM ELEMENTS

INTEGRATED CONTROL SYSTEM FOR A GAS TURBINE ENGINE

ENGINE SYSTEM

Provided is an engine system capable of promptly dealing with the occurrence of failure in a power supply part or operation control part. The engine system comprises: an engine 40 for outputting shaft power by burning fuel G; a system body 30 operating by using the shaft power of the engine 40; an operation control part A; and a power supply part B for converting commercial power into operating power and supplying the operating power to the operation control part A. The power supply part B comprises a system body-side power supply part 15 and an engine-side power supply part 25 separate from each other, the system body-side power supply part 15 supplying operating power for controlling operation of the system body 30, and the engine-side power supply part 25 supplying operating power for controlling operation of the engine 40.

METHOD AND APPARATUS FOR CONTROLLING THE COMBUSTION IN A GAS TURBINE

A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring , by means of one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel by means of at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, hav-ing a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and vari-able with time.

MODEL BASED FUEL-AIR RATIO CONTROL

A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to estimate combustor fuel-air ratio based on a realtime model-based estimate of combustor airflow, and commands engine actuators to correct for a difference between the estimated combustor fuel-air ratio and a limit fuel-air ratio selected to avoid lean blowout.

MODEL-BASED COMBINED CYCLE POWER PLANT LOAD CONTROL

A control system uses a modeled steam turbine megawatt (power) change attributed to a gas turbine demand change (i.e., a steam turbine to gas turbine transfer function) within a conventional closed loop feedback control scheme to perform control of a combined cycle power plant. This control system implements a form of internal model control and provides better unit megawatt (power) set-point tracking and disturbance variable rejection for overall more robust control, and thus operates to optimize the gas turbine operation of the combined cycle power plant in a manner that provides cost savings over time.

ULTRASOUND FUEL FLOW SENSING AND CONTROL

Methods and apparatus for measuring liquid fuel flows within a conduit (104) are disclosed. An example flow sensor (101) may include a conduit (104) arranged to flow fuel therethrough along a flow axis (154), the conduit (104) defining a flow area orthogonal to the flow axis (154). The flow sensor (101) may further include a first transducer (102) arranged to direct a first signal through the conduit (104) proximate the flow area (152) to a second transducer (114), the second transducer (114) being arranged to direct a second signal through the conduit (104) proximate the flow area (152) to the first transducer (102), the first transducer (102) being spaced apart from the second transducer (114) by a signal path length (112), and in a direction parallel to the flow axis (154) by an axial distance. The fuel flow measuring system (100) may further include a processor (180) arranged to calculate a fuel mass flow rate (170) based on first and second signal transit times (122, 118), known fuel ...

CONTROL AND MONITORING SYSTEM AND METHOD FOR AIRCRAFT EQUIPMENT

Système (2) de commande et de surveillance d'équipements d'un aéronef, chaque équipement étant apte à être commuté entre deux valeurs d'état logique d'activation, comprenant une interface homme machine (16), un module (40) de configuration d'un état fonctionnel d'activation d'une fonction propre à être réalisée au moins équipements d'un système de l'aéronef, l'état fonctionnel d'activation étant configurable entre un état actif et un état inactif, ledit module (40) de configuration étant adapté pour détecter une action de sélection d'un état fonctionnel d'activation de ladite fonction par un opérateur, et un module (44) de commande et de surveillance configuré pour déterminer un état logique d'activation de chacun desdits équipements dudit système, de telle sorte que, lorsque chacun desdits équipements est dans l'état logique d'activation déterminé, ladite fonction soit dans l'état fonctionnel d'activation sélectionné.

OVERSPEED PROTECTION DEVICE OF AN AIRCRAFT ENGINE

L'invention concerne un dispositif de protection contre survitesse d'un moteur d'un aéronef.

SYSTEMS AND METHODS FOR CLOSED LOOP EMISSIONS CONTROL

Certain embodiments of the invention may include systems and methods for controlling combustion emission parameters associated with a gas turbine combustor (104). The method can include providing an optical path through a gas turbine (106) exhaust duct (110), propagating light along the optical path, measuring exhaust (108) species absorption of the light within the gas turbine (106) exhaust duct (110), and controlling at least one of the combustion parameters based at least in part on the measured exhaust (108) species absorption.

MONITORING OF A FILTER OF THE FUEL-SUPPLY SYSTEM OF AN AIRCRAFT ENGINE

Procédé de surveillance d'un filtre (3) du circuit d'alimentation (1) en carburant d'un moteur d'aéronef, comprenant; - une étape de détection d'un colmatage du filtre, et - une étape d'envoi d'un message d'indication, caractérisé en ce qu'il comprend : - une étape de détermination d'une phase courante parmi une pluralité de phases successives d'une mission de l'aéronef, comprenant au moins une phase pendant laquelle le colmatage du filtre n'est pas susceptible d'être causé par le givre et une phase pendant laquelle le colmatage du filtre est susceptible d'être causé par le givre, et - en réponse à la détection d'un colmatage, une étape de détermination d'un type de colmatage en fonction de ladite phase courante, dans lequel, lors de l'étape d'envoi d'un message d'indication, le message envoyé dépend du type de colmatage.

AIRCRAFT POWER OUTTAKE MANAGEMENT

A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.

BURNER FOR A CAN COMBUSTOR

The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device, wherein the mixing and injection device is comprising a limiting wall that defines a gas-flow channel and at least two streamlined bodies (22), each extending in a first transverse direction into the gas-flow channel. Each streamlined body (22) had two lateral surfaces that are arranged essentially parallel to the main-flow direction (14), the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body (22). Each streamlined body (22) has a cross-section perpendicular to the first transverse direction (49) that is shaped as a streamlined profile. At least one of said streamlined bodies (22) is provided with a mixing structure and with at least one fuel nozzle located at its trailing edge for introducing at least one fuel essentially parallel to the main-flow ...

ROTOR RESONANCE DISTURBANCE REJECTION CONTROLLER

A speed control system for an engine comprising at least one rotary load is provided. The speed control system may include a rotor speed controller configured to regulate speed in the rotary load based on a sensed rotor speed, exclusive of resonant mode speed oscillations, in closed loop feedback with a commanded rotor speed. To provide active damping of resonant mode speed oscillations, a resonance disturbance rejection controller may be configured to compensate a speed control signal by observing a component of the sensed rotor speed that is due to resonant mode oscillations. Based on the observed resonance component, the resonance disturbance rejection controller may compute an adjustment value for the speed control signal. In the particular case of gas turbine engines, the resonance disturbance rejection controller may effect active damping by compensation of a fuel flow request for a gas generator.

CONTROL PROCESS AND REGULATION SYSTEM FOR SUPPLYING COMPRESSED AIR TO A COMPRESSED AIR NETWORK, SPECIFICALLY IN AN AIRCRAFT

L'invention permet de s'affranchir des compresseurs de charge surdimensionnés pour fournir de l'air comprimé à un réseau pneumatique, en particulier au réseau d'un aéronef. Ce surdimensionnement absorbe les fortes pertes de charge générées par la régulation des vannes IGV d'accès d'air à ce compresseur. Pour palier ce problème, la gestion des variations des débits d'air prélevé est basée par une éjection régulée du surplus d'air non consommé par le réseau. Un système de fourniture d'air comprimé (1) à un réseau pneumatique (2) comporte un compresseur de charge (10), une alimentation en air (4) et un arbre de puissance (11) entraînant le compresseur de charge (10). Selon l'invention, il comporte également, en sortie d'air de ce compresseur de charge (10), un canal de liaison (6a) relié, d'une part, à un canal (6b) de connexion au réseau pneumatique (2) et, d'autre part, à un conduit d'évacuation d'air (6c) vers une tuyère d'échappement (34). Des vannes de prélèvement de débit d'air (12, ...

VIBRATION ISOLATION MOUNT SYSTEM

VIBRATION ISOLATION MOUNT SYSTEM

In a fuel control, the body of a feedback resolver is isolated from vibratory fields within a housing in which it is mounted while maintaining alignment of its gear with a fuel control linkage. The resolver is isolated by disposing a first means radially about the feedback device, disposing a second means between the bottom of the feedback device and the housing and disposing a third means at the top of the housing, the means at the top of the housing and at the bottom of the housing being compressed such that the resolver maintains its axial relationship with the fuel control linkage while isolating the resolver from vibratory fields encountered within the housing.

APPARATUS AND METHOD FOR COMBUSTION TURBINE GENERATOR OVERFUEL LIMITING

... 54,323 A combustion turbine-generator is controlled for preventing firing (or cycle) temperatures therein from exceeding a predetermined limit by regulating a flow of fuel to such combustion turbine by the steps of generating a multidimensional data base having at least three variables including: compressor inlet air temperature, compressor inlet guide vanes' position, and generator load limit: (2) storing the multidimensional data base in a digital computer; (3) monitoring the compressor inlet air temperature and the compressor inlet guide vanes' position with sensors; (4) operating the digital computer, with the multidimensional data base stored therein, to receive from the sensors a pair of signals that are indicative of the compressor inlet air temperature and the compressor inlet guide vanes' position, and to periodically determine a unique data point upon a surface of the multidimensional data base that corresponds to the monitored compressor inlet air temperature, the monitored compressor ...

Installation d'alimentation en combustible d'un moteur à combustion interne

Einrichtung zum Regulieren der Brennstoffzufuhr einer Gasturbinenanlage.

Chambre de combustion pour turbine à gaz

Einrichtung zur Regelung der Kraftstoffzuführung in Gasturbinenanlagen

Treibstoffzufuhr-Steuermechanismus für einen Nachbrenner eines Gasturbinentriebwerks

Installation à turbine à gaz

Method and system for a burn fashion transition in a gas turbine.

Erfindungsgemäss werden ein Verfahren, ein System (120) und ein Gasturbinensystem für den Übergang zwischen Verbrennungsmodi in einer Gasturbine bereitgestellt. Ein Prozessor erzeugt Daten, die für einen ursprünglichen Satz Splits stehen, um Kraftstoff und/oder Luft zu mindestens einer Brennkammer in der Gasturbine zu leiten. Ein Gasturbinenmodellmodul (510) erzeugt Daten, die für mindestens eine Turbinenbetriebsbedingung stehen. Ein erstes Splitberechnungsmodul (512) erzeugt Daten, die für mindestens einen Satz aktiver Steuersplits stehen, zur Steuerung der Gasturbine in einem ersten Verbrennungsmodus, wobei als eine Eingabe die ursprünglichen Splitdaten verwendet werden. Ein zweites Splitberechnungsmodul (514) erzeugt Daten, die für mindestens einen Satz passiver Steuersplits stehen, zur Steuerung der Gasturbine in mindestens einem zweiten Verbrennungsmodus. Der Übergang zwischen Verbrennungsmodi kann durch die Verwendung mindestens eines der aktiven Steuersplits und der passiven Steuersplits ...

Method and system for a burn fashion transition in a gas turbine.

Erfindungsgemäss werden ein Verfahren, ein System (120) und ein Gasturbinensystem für den Übergang zwischen Verbrennungsmodi in einer Gasturbine bereitgestellt. Ein Prozessor erzeugt Daten, die für einen ursprünglichen Satz Splits stehen, um Kraftstoff und/oder Luft zu mindestens einer Brennkammer in der Gasturbine zu leiten. Ein Gasturbinenmodellmodul (510) erzeugt Daten, die für mindestens eine Turbinenbetriebsbedingung stehen. Ein erstes Splitberechnungsmodul (512) erzeugt Daten, die für mindestens einen Satz aktiver Steuersplits stehen, zur Steuerung der Gasturbine in einem ersten Verbrennungsmodus, wobei als eine Eingabe die ursprünglichen Splitdaten verwendet werden. Ein zweites Splitberechnungsmodul (514) erzeugt Daten, die für mindestens einen Satz passiver Steuersplits stehen, zur Steuerung der Gasturbine in mindestens einem zweiten Verbrennungsmodus. Der Übergang zwischen Verbrennungsmodi kann durch die Verwendung mindestens eines der aktiven Steuersplits und der passiven Steuersplits ...

Method and apparatus for rapidly detecting the [...] of fuel.

Die Erfindung betrifft eine Sensorvorrichtung (120) und Verfahren zum Ermöglichen der Verbrennung eines gasförmigen Brennstoffs. Die Sensorvorrichtung (120) weist eine Verbrennungsvorrichtung auf, die in ihr eine Brennkammer definiert. Die Verbrennungsvorrichtung ist zur Verbrennung eines Brennstoff-Luft-Gemischs in der Brennkammer gestaltet, um wenigstens ein Verbrennungsprodukt zu erzeugen. Mit der Verbrennungsvorrichtung ist wenigstens eine optische Diagnosevorrichtung zum Messen von wenigstens einer Eigenschaft des wenigstens einen Verbrennungsprodukts in der Brennkammer gekoppelt. Eine Steuereinheit (118) ist mit der wenigstens einen optischen Diagnosevorrichtung gekoppelt und ist zur Ermittlung des Wobbeindexes des Brennstoffs in Echtzeit auf der Basis der gemessenen wenigstens einen Eigenschaft des wenigstens einen Verbrennungsprodukts und von in der Steuereinheit (118) gespeicherten vorbestimmten Verbrennungszustandsdaten konfiguriert.

Fuel- Vorerwärmungsvorrichtung having first and second water supply.

Es ist ein Brennstoff-Vorerwärmungsvorrichtung geschaffen, die eine erste und eine zweite Wasserzufuhr (70, 100) zum Zuführen einer ersten Wassermenge mit einer ersten Temperatur und einer zweiten Wassermenge mit einer zweiten, gegenüber der ersten Temperatur niedrigeren Temperatur, einen Wärmetauscher (90), der mit den Wasserzufuhren (70, 100) gekoppelt ist und durch den einerseits Brennstoff sowie andererseits ein Gemisch aus den Wassermengen der Wasserzufuhren strömen, und eine Steuereinrichtung enthält, die betriebsmässig zwischen den Wasserzufuhren (70, 100) und dem Wärmetauscher (90) eingefügt ist, um die der jeweiligen Wasserzufuhr (70, 100) entnommene und dem Wärmetauscher zuzuführende erste und zweite Wassermenge so zu wählen und/oder abzustimmen, um den Brennstoff auf eine Temperatur zu erwärmen, um eine modifizierte Wobbeindex (MWI)-Vorgabe zu erfüllen.

Gas turbine system with multi-cycle distributor for combustion chamber combustion chamber fashion uncoupling by means of allocations of fuel on combustion chamber tubing level.

Gemäss einem Aspekt der Erfindung ist ein Gasturbinensystem (100) geschaffen. Das Gasturbinensystem (100) enthält einen Verdichter (110), der dazu eingerichtet ist, Luft zu verdichten (115) und Brennkammerrohre (120), die in Strömungsverbindung mit dem Verdichter (110) stehen, wobei die Brennkammerrohre (120) dazu eingerichtet sind, verdichtete Luft (115) aus dem Verdichter (110) aufzunehmen, und einen Brennstoffstrom zu verbrennen. Das Gasturbinensystem (100) enthält ferner einen Mehrkreislaufverteiler (200), der mit den Brennkammerrohren (120) verbunden ist und der dazu eingerichtet ist, anhand des Brennstoffstroms den Brennkammerrohren (120) einen aufgeteilten Brennstoffstrom zu liefern.

Heissund sources of warm water containing fuel heating system.

Es ist ein System geschaffen, das eine erste und eine zweite Wasserzufuhr (70, 100) mit einer ersten und einer zweiten relativ hohen bzw. niedrigen Temperatur, einen Wärmetauscher (90), der mit den Wasserzufuhren (70, 100) gekoppelt ist und durch den Brennstoff sowie relative Mengen der Wasserzufuhren mit der ersten und der zweiten Temperatur zur Brennstofferwärmung strömen, und eine Steuereinrichtung enthält, die betriebsmässig zwischen den Wasserzufuhren (70, 100) und dem Wärmetauscher (90) eingefügt ist, um die relativen Mengen der Wasserzufuhren (70, 100) zu wählen und/oder abzustimmen, denen gestattet wird, durch den Wärmetauscher (90) zu strömen, um den Brennstoff auf eine Temperatur zu erwärmen, die auf einer Heizanforderung beruht, um eine modifizierte Wobbeindex(MWI)-Vorgabe zu erfüllen.

Lean Blowout Auslöschschutz by regulation of nozzle equivalence conditions.

Es wird ein Verfahren und ein System offenbart, um eine Brennkammer einer Gasturbine anhand des Äquivalenzverhältnisses der Brennstoffdüsen zu steuern. Das Äquivalenzverhältnis mindestens einer Brennstoffdüse (12) der Brennkammer wird gemessen, wobei die Brennkammer mindestens eine Brennstoffdüse (12) aufweist, die in mindestens einem Brennkammerrohr (10) angeordnet ist. Das gemessene Äquivalenzverhältnis wird einem Schwellenwert für den Lean-Blowout verglichen. Der Brennstoffstrom aus der mindestens einen Düse (12) wird modifiziert, wodurch das Äquivalenzverhältnis angepasst wird, um den Lean-Blowout zu verhindern.

Gas turbine system with recycling of exhaust gases as well as procedure for the enterprise of such a plant.

Eine Gasturbinenanlage (10) mit Abgasrückführung umfasst eine Hauptgasturbine (11, 12, 13) mit einem Hauptverdichter (11) und einer Hauptturbine (12), welche einen Hauptgenerator (14) antreiben, sowie eine Brennkammer (16), deren Ausgang mit dem Eingang der Hauptturbine (12) der Hauptgasturbine verbunden ist, eine Brennstoffzufuhr (18) aufweist und über die Hochdruckseite eines Rekuperators (15) Verbrennungsluft vom Ausgang des Hauptverdichters (11) der Hauptgasturbine erhält, wobei der Ausgang der Hauptturbine (12) und der Eingang des Hauptverdichters (11) der Hauptgasturbine zur Abgasrückführung über die Niederdruckseite des Rekuperators (15) und einen Kühler (17) verbunden sind, und wobei auf der Niederdruckseite des Rekuperators (15) eine Ladegruppe (36) mit einem Verdichter (23) und einer Turbine (24) angeordnet ist, welche Ladegruppe (36) über einen Lufteinlass (20) Luft ansaugt und mit dem Ausgang ihres Verdichters (23) an den Ausgang der Niederdruckseite des Rekuperators (15) und ...

Procedure for CO emission arms the enterprise of a gas turbine with sequential burn and gas turbine with improved part-load emission behavior.

Die Erfindung betrifft ein Verfahren zum CO-emissionsarmen Teillastbetrieb einer Gasturbine mit sequentieller Verbrennung, wobei die Luftzahl () der operativen Brenner (9) der zweiten Brennkammer (15) bei Teillast unter einer maximalen Luftzahl ( max ) gehalten wird, sowie eine Gasturbine zur Ausführung des Verfahrens. Um die maximale Luftzahl () zu reduzieren, werden eine Reihe von Modifikationen im Betriebskonzept der Gasturbine einzeln oder in Kombination durchgeführt. Eine Modifikation ist ein Öffnen der verstellbaren Verdichterleitschaufelreihe (14) vor Einschalten der zweiten Brennkammer (15). Zum Einschalten der zweiten Brennkammer wird die verstellbare Verdichterleitschaufelreihe (14) schnell geschlossen und synchronisiert Brennstoff in die Brenner (9) der zweiten Brennkammer (15) eingeleitet. Eine weitere Modifikation ist das Ausschalten von einzelnen Brennern (9) bei Teillast.

turbine control system and power generating system.

Es wird ein Turbinensteuerungssystem bereitgestellt, das das Unterfrequenzverhalten von Gasturbinen mit Hilfe einer schnell reagierenden Leistungserhöhung verbessert. Das System umfasst einen Speicher (112), der eine Mischung von Antriebsbrennstoff wie zum Beispiel Ethanol oder Methanol und entmineralisiertem Wasser in einem vorgegebenen Verhältnis unter Druck speichert, welches dem Gasturbinenkompressor (122) bereitgestellt wird, um den Massenstrom zur Turbine zu erhöhen, wenn ein Sensor einen Unterfrequenzzustand des Stromnetzes feststellt.

System and procedure for the determination of an exhaust goal temperature for a gas turbine.

Die Erfindung betrifft ein System und ein Verfahren zum Bestimmen einer Sollabgastemperatur für eine Gasturbine (10). Das Verfahren beinhaltet die Bestimmung einer Sollabgastemperatur wenigstens zum Teil auf der Basis eines Verdichterdruckzustandes; der Bestimmung einer Temperaturanpassung an die Sollabgastemperatur wenigstens zum Teil auf der Basis einer Dampffeuchtigkeit; und einer Änderung der Sollabgastemperatur wenigstens zum Teil auf der Basis der Temperaturanpassung.

System and method for determining an exhaust gas-target temperature for a gas turbine.

Die Erfindung betrifft ein System und ein Verfahren zum Bestimmen einer Sollabgastemperatur für eine Gasturbine (10). Das Verfahren beinhaltet die Bestimmung einer Sollabgastemperatur wenigstens zum Teil auf der Basis eines Verdichterdruckzustandes; der Bestimmung einer Temperaturanpassung an die Sollabgastemperatur wenigstens zum Teil auf der Basis einer Dampffeuchtigkeit; und einer Änderung der Sollabgastemperatur wenigstens zum Teil auf der Basis der Temperaturanpassung.

Method, apparatus and system for determining a target exhaust temperature for a gas turbine.

Die Erfindung betrifft eine Vorrichtung, ein System und ein Verfahren zum Bestimmen einer Sollabgastemperatur für eine Gasturbine (10). Das Verfahren beinhaltet die Festlegung einer Sollabgastemperatur wenigstens zum Teil auf der Basis eines Verdichterdruckzustandes; die Festlegung eines Werts einer Temperaturanpassung für die Sollabgastemperatur wenigstens zum Teil auf der Basis einer Dampffeuchtigkeit; und eine Änderung der Sollabgastemperatur wenigstens zum Teil auf der Basis des Werts der Temperaturanpassung.

[...] with integrated Liquid evaporator.

Die vorliegende Erfindung stellt eine Brennstoffdüse (100) für eine Gasturbine bereit, die einen Primärbrennstoff und einen Sekundärbrennstoff verwendet. Die Brennstoffdüse (100) enthält eine Anzahl von Primärbrennstoffeinspritzanschlüssen (170) für den Primärbrennstoff, einen Wasserdurchgang (220), eine Anzahl von Sekundärbrennstoffeinspritzanschlüssen (280) und ein Sekundärbrennstoffverdampfungssystem zum Zerstäuben des Sekundärbrennstoffs.

Fuel nozzle.

Die vorliegende Erfindung stellt eine Brennstoffdüse (100) für eine Gasturbine bereit, die einen Primärbrennstoff und einen Sekundärbrennstoff verwendet. Die Brennstoffdüse (100) umfasst eine Anzahl von Primärbrennstoffeinspritzanschlüssen (170) für den Primärbrennstoff, einen Wasserdurchgang (220), eine Anzahl von Sekundärbrennstoffeinspritzöffnungen (280) und ein Sekundärbrennstoffverdampfungssystem zum Zerstäuben des Sekundärbrennstoffs.

multi-cycle distributor gas turbine system.

Das erfindungsgemässe Gasturbinensystem (100) enthält einen Verdichter (110), der dazu eingerichtet ist, Luft zu verdichten (115) und Brennkammerrohre (120), die in Strömungsverbindung mit dem Verdichter (110) stehen, wobei die Brennkammerrohre (120) dazu eingerichtet sind, verdichtete Luft (115) aus dem Verdichter (110) aufzunehmen, und einen Brennstoffstrom zu verbrennen. Das Gasturbinensystem (100) enthält ferner einen Mehrkreislaufverteiler (200), der mit den Brennkammerrohren (120) verbunden ist und der dazu eingerichtet ist, aus dem Brennstoffstrom den Brennkammerrohren (120) einen aufgeteilten Brennstoffstrom zu liefern.

Control system for a gas turbine engine arrangement and gas turbine engine arrangement

Ein Steuerungssystem wird geschaffen. Ein Steuerungssystem schliesst ein Regelungsmodul (116), das angepasst ist, einen Brennstoffzufuhrdruck für eine Gasturbine zu regeln, einen Druckmessfühler (108), der angepasst ist, einen Druck von der Gasturbine zugeführtem Brennstoff zu erfassen, eine Brennstoffzufuhrleitung und ein Rückkopplungsmodul (117) ein, welches eine Rückkopplung einschliesst, wobei das Rückkopplungsmodul (117) angepasst ist, ein positives Rückkopplungs-Referenzsignal an das Regelungsmodul (116) zu liefern, so dass eine Reaktionszeit des Steuerungssystems auf Änderungen im Brennstoffdruck reduziert wird.

Gas turbine and efficiency bonus plan.

Eine Gasturbine (100) wird geschaffen, die an ein elektrisches Netz gekoppelt ist, das bei einem standardisierten Netzfrequenzwert arbeitet, wobei die Gasturbine (100) eine Brennkammer (104) einschliesst, die in Strömungsverbindung mit einer Vielzahl von unabhängigen Brennstoffkreisen (110) und einem Kompressor (102) gekoppelt ist. Die Gasturbine (100) enthält ferner einen Sensor zur Erfassung einer Abweichung einer Netzfrequenz von dem standardisierten Netzfrequenzwert; und ein Steuergerät zur Einstellung des Brennstoffflusses in Reaktion auf die Abweichung der Netzfrequenz, welches dazu ausgelegt ist, den Brennstofffluss von einem Teil der Vielzahl von unabhängigen Brennstoffkreisen (110) einzustellen und einen im Wesentlichen konstanten Luftfluss von dem Kompressor (102) aufrechtzuerhalten, so dass ein Verhältnis von Brennstoff- zu Kompressorentladedruck derart geregelt ist, dass ein Nacheilen des Brennkammerzustandes auf Änderungen des Luftflusses unterbunden ist, wenn eine Reaktion ...

CONTROL SYSTEM AND METHOD POWER PLANT

method and device for feeding a turbomachine combustion chamber with a regulated flow of fuel

High-pressure fuel is supplied at a controlled rate to a combustion chamber via a position-controlled valve and a variable-restriction stop-and-pressurizing cut-off valve. A value representative of the real mass flow rate of fuel as delivered is calculated by a calculation unit on the basis of information representative of the pressure difference between the inlet and the outlet of the cut-off valve and of the flow section through the cut-off valve, e.g. as represented by the position X of the slide of the cut-off valve. The position-controlled valve has a variable position that is controlled by the calculation unit as a function of the difference between the calculated value representative of the real mass flow rate and a value representative of a desired mass flow rate.

Distributed small engine fadec

A full authority digital engine controller (FADEC) controls an engine attached to an airframe. The FADEC includes an electronic engine controller (EEC) attached to the engine, an airframe data concentrator (ADC) attached to the airframe, and a digital data bus electrically connecting the ADC to the EEC. The ADC is electrically connected to a plurality of airframe sensors to convert the airframe sensor signals to airframe sensor digital data. The digital bus conducts the airframe sensor digital data to the EEC.

Method of controlling speed transients in a turbine engine

A method of controlling an engine in which a fuel flow setpoint is determined, the method comprising: a step of implementing a steady speed regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a setpoint parameter that depends on the position of a control lever and an operating parameter of the engine; wherein the method comprises: a detection step of detecting an intended speed transient; and in response to said detection step, a step of implementing a speed transient regulation loop in which the fuel-flow-rate setpoint is determined as a function of a difference between a speed of the engine and a speed setpoint varying over time with the speed trajectory as generated in predetermined manner.

METHOD FOR SWITCHING OVER A COMBUSTION DEVICE

An exemplary method for switching over a combustion device from operation with a first premix fuel to a second premix fuel includes reducing and stopping a first premix fuel supply and then starting a second premix fuel supply. In an intermediate phase, after the first premix fuel supply stop and before the second premix fuel supply start, the combustion device is operated with one or more pilot fuels generating diffusion flames. 1. A method for switching over a combustion device from operation with a first premix fuel to a second premix fuel comprising:reducing and stopping a first premix fuel supply;operating the combustion device with at least one pilot fuel that generates diffusion flames; andstarting a second premix fuel supply following generation of the diffusion flames.2. The method according to claim 1 , wherein the pilot fuels include first and second pilot fuels claim 1 , which are fed to the combustion device during operation of the combustion device.3. The method according to claim 2 , wherein in an intermediate phase claim 2 , after the first premix fuel supply stops and before the second premix fuel supply starts claim 2 , the combustion device is operated with the at least one pilot fuel generating only diffusion flames.4. The method according to claim 3 , wherein only the first and second pilot fuels support combustion device operation during the intermediate phase.5. The method according to claim 2 , comprising:injecting the first and the second pilot fuels together with the first premix fuel and the second premix fuels.6. The method according to claim 3 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.7. The method according to claim 5 , comprising:starting the first pilot fuel supply before the second pilot fuel supply starts.8. The method according to claim 3 , comprising:terminating the first pilot fuel supply before the second pilot fuel supply terminates.9. The method according to claim 5 , ...

Method and a device for producing a setpoint signal

A method and device producing a setpoint signal representing a flow rate of fuel that a metering unit having a slide valve is to supply to a fuel injection system of a combustion chamber in a turbine engine, the position of the valve depending on the setpoint signal. The method: obtains a first signal representing a measurement as delivered by a flow meter of a flow rate of fuel injected into the chamber; evaluates a second signal representing the flow rate of fuel injected into the chamber based on a measurement of the position of the valve; estimates a third signal representative of the measurement delivered by the flow meter by applying a digital model of the flow meter to the second signal; and produces the setpoint signal by adding a compensation signal to the first signal, the compensation signal obtained by subtracting the third signal from the second signal.

Method for Operating a Gas Turbine

In a method for operating a gas turbine (), a CO2-containing gas is compressed in a compressor (), the compressed gas is used to burn a fuel in at least one subsequent combustion chamber (), and the hot combustion gases are used to drive at least one turbine (). Improved control and performance can be achieved by measuring the species concentration of the gas mixture flowing through the gas turbine () at several points within the gas turbine () by a distributed plurality of species concentration sensors (-), and utilizing the measured concentration values to control the gas turbine () and/or optimize the combustion performance of the gas turbine (). 1. A method for operating a gas turbine , in which turbine a CO-containing gas is compressed in a compressor , the compressed gas is used to burn a fuel in at least one subsequent combustion chamber to form hot combustion gases , and the hot combustion gases are used to drive at least one turbine , the method comprising:measuring the species concentration of the gas mixture flowing through the gas turbine at several points within the gas turbine with a distributed plurality of species concentration sensors; andcontrolling the gas turbine, optimizing the combustion performance of said gas turbine, or both, based on the measured species concentration values.2. A method according to claim 1 , wherein measuring comprises:{'sub': '2', 'measuring at least the Oconcentration with said plurality of species concentration sensors.'}3. A method according to claim 1 , wherein said species concentration sensors comprise ZrOsensors.4. A method according to claim 1 , wherein said species concentration sensors consist of ZrOsensors.5. A method according to claim 1 , in which the gas turbine is a sequential-combustion turbine with two combustors claim 1 , two turbines claim 1 , and flue gas recirculation claim 1 , and in which at least part of the flue gas at an exit of the gas turbine is recirculated and enters the compressor after ...

Method for operating a combustion device during transient operation

A method and apparatus are disclosed for operating a combustion device during a transient operation. The combustion device is fed with at least a fuel. The transient operation includes a period having a period length (T) during which the fuel is fed in an amount lower that a designated (e.g., critical) amount (Mc). A limit value (L) is defined for the period length (T), and fuel feed is regulated to keep the period length (T) smaller or equal to the limit value (L).

Method and apparatus for optimizing the operation of a turbine system under flexible loads

A gas turbine system includes a compressor protection subsystem; a hibernation mode subsystem; and a control subsystem that controls the compressor subsystem and the hibernation subsystem. At partial loads on the turbine system, the compressor protection subsystem maintains an air flow through a compressor at an airflow coefficient for the partial load above a minimum flow rate coefficient where aeromechanical stresses occur in the compressor. The air fuel ratio in a combustor is maintained where exhaust gas emission components from the turbine are maintained below a predetermined component emission level while operating at partial loads.

Multi-spool intercooled recuperated gas turbine

A method and apparatus are disclosed for a multi-spool gas turbine engine with a variable area turbine nozzle and a motor/alternator device on the highest pressure turbo-compressor spool for starting the gas turbine and power extraction during engine operation. During power down of the engine, the variable area turbine nozzle may be used in conjunction with power extraction to maintain a near constant combustor outlet temperature while controlling turbine inlet temperatures on the turbines downstream of the highest pressure turbine and controlling spool speed on the highest pressure turbine.

Method for optimizing the control of a free turbine power package for an aircraft, and control for implementing same

A method optimizing fuel-injection control with driving speeds of apparatuses adjusted by controlling a turbine speed according to power, and optimizing control of a free turbine power package of an aircraft, including a low-pressure body, supplying power to apparatuses and linked to a high-pressure body. The method varies the low-pressure body speed to obtain a minimum speed for the high-pressure body, so power supplied by the apparatuses remains constant. Power supplied by the apparatuses is dependent upon the apparatuses driven speed by the low-pressure body, and a speed set point of the low-pressure body is dependent upon a maximum value of minimum speeds of the apparatuses, enabling required power to be optimized, upon a positive or zero incrementation added to the speed set point of the low-pressure body to minimize speed of the high-pressure body to the apparatuses power supply.

Fuel Flow Control Method and Fuel Flow Control System of Gas Turbine Combustor for Humid Air Gas Turbine

Provided is a fuel flow control method of a gas turbine combustor provided in a humid air gas turbine, by which method NOx generation in the gas turbine combustor is restricted before and after the starting of humidification and combustion stability is made excellent. 1. A fuel flow control method of a gas turbine combustor provided in a humid air gas turbine comprising a compressor , the gas turbine combustor , in which a fuel is burned with the use of a compressed air compressed by the compressor to generate a combustion gas , a turbine driven by a combustion gas generated in the gas turbine combustor , and a humidifier for humidifying a compressed air compressed by the compressor and supplied to the gas turbine combustor , the gas turbine combustor comprising a plurality of combustion sections comprised of a plurality of fuel nozzles for supplying of a fuel and a plurality of air flow passages for supplying of a combustion air , a part of the plurality of combustion sections provided in the gas turbine combustor being formed into a combustion section or sections , which are more excellent in flame holding performance than the remaining combustion sections , in which method fuel ratios of fuels , respectively , supplied to the plurality of combustion sections of the gas turbine combustor are controlled on the basis of deviation between a load command and electric power generation ,the method comprising controlling a fuel flow rate to the combustion sections in the gas turbine combustor through evaluating a moisture content in a combustion air supplied to the gas turbine combustor on the basis of a humidification water quantity and an air temperature after humidification in the humidifier, using a combustion air flow rate supplied to the gas turbine combustor to evaluate a combustion temperature in the combustion sections, and regulating a fuel ratio of a fuel flow rate supplied to the combustion section or sections of excellent flame holding performance and a fuel ...

Fluid flow control device and method

A fluid flow control system includes a fluid inlet, a central chamber, a first nozzle extending from a first side of the central chamber and comprising a first throat, a second nozzle extending from a second side of the central chamber opposite the first side and comprising a second throat, and a flow control shuttle. The flow control shuttle includes a first needle having a first tapered portion positioned within the first throat for controlling flow through the first nozzle and a second needle having a second tapered portion positioned within the second throat for controlling flow through the second nozzle.

CONTROL OF A FUEL METERING DEVICE FOR TURBOMACHINE

A control of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint includes responding to at least one validity criterion to select a weight flow rate from among: a weight flow rate calculated as a function of a position signal; a weight flow rate calculated as a function of the position signal and of at least one temperature measurement signal; a weight flow rate calculated as a function of the position signal and of at least one permittivity measurement signal; a weight flow rate calculated as a function of the position signal, of at least one temperature measurement signal, and of at least one permittivity measurement signal; and a weight flow rate calculated as a function of a temperature measurement signal, of a permittivity measurement signal, and of a volume flow rate measurement signal. 110-. (canceled)11. A method of controlling a position of a slide of a fuel metering device for a turbine engine as a function of a weight flow rate setpoint , the method comprising:obtaining a position signal coming from a sensor configured to measure a position of the slide;obtaining at least one measurement signal coming from a flow meter configured to measure a fuel flow rate in the flow meter;estimating at least one validity criterion for the at least one measurement signal;determining a fuel weight flow rate through the flow meter; andcontrolling the position of the slide as a function of the determined weight flow rate and of the weight flow rate setpoint;the at least one measurement signal comprises first and second fuel temperature measurement signals, first and second fuel permittivity measurement signals, and first and second fuel volume flow rate measurement signals; and a weight flow rate calculated as a function of the position signal;', 'a weight flow rate calculated as a function of the position signal and of at least one of the temperature measurement signals;', 'a weight flow rate calculated as a function of the position ...

Methods of Operation of A Gas Turbine With Improved Part Load Emissions Behavior

In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (λ) of the operative burners () of the second combustor () is kept below a maximum air ratio (λ) at part load In order to reduce the maximum air ratio (λ), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes () before engaging the second combustor (). For engaging the second combustor, the row of variable compressor inlet guide vanes () is quickly closed and fuel is introduced in a synchronized manner into the burner () of the second combustor (). A further modification is the deactivating of individual burners () at part load. 1. A method for the low-CO emissions operation of a gas turbine with sequential combustion , wherein the gas turbine includes a first turbine , a second turbine , at least one compressor , a first combustor which is connected downstream to the compressor and the hot gases of which first combustor are admitted to the first turbine , and a second combustor which is connected downstream to the first turbine and the hot gases of which are admitted to the second turbine , the second combustor including operative burners each having an air ratio (λ) , the method comprising:{'sub': 'max', 'maintaining the air ratio (λ) of the operative burners of the second combustor below a maximum air ratio (λ).'}2. The method as claimed in claim 1 , further comprising:{'b': '2', 'shutting off a fuel feed to at least one burner of the second combustor at part load so that, with an unaltered turbine inlet temperature of the second turbine (TIT), an air ratio (λ) of the burners in operation is reduced.'}3. The method as claimed in claim 2 , wherein:the second combustor includes a parting plane; andshutting off a fuel feed to at least one burner of the second combustor at part load comprises first shutting ...

AUTOMATED TUNING OF GAS TURBINE COMBUSTION SYSTEMS

A system for tuning the operation of a gas turbine is provided based on measuring operational parameters of the turbine and directing adjustment of operational controls for various operational elements of the turbine. A controller is provided for communicating with sensors and controls within the system. The controller receiving operational data from the sensors and comparing the data to stored operational standards to determining if turbine operation conforms to the standards. The controller then communicates selected adjustment in an operational parameter of the turbine. The controller then receives additional operational data from the sensors to determine if an additional adjustment is desired or is adjustment is desired of a further selected operational parameter. 1. A system for tuning the operation of a gas turbine , the turbine having sensors for measuring operational parameters of the turbine , the operational parameters including combustor dynamics , and turbine exhaust emissions , the turbine also having operational controls for adjusting various operational control elements of the turbine , the operational control elements comprising the turbine fuel distribution splits , the inlet fuel temperature , and fuel-air ratio , and a communication link for the sensors and controls , the system comprising: receiving operational data regarding the operational parameters including combustor dynamics and turbine exhaust emissions from the sensors,', 'comparing the operational data to stored operational standards and determining if turbine operation conforms to the operational standards, the operational standards based on operational priorities,', 'communicating with the operational controls to perform a selected adjustment in an operational control element of the turbine,', 'receiving operational data from the sensors upon communicating the selected adjustment to determine if an additional incremental adjustment is desired, and', 'upon completing a series of ...

Exhaust temperature based threshold for control method and turbine

A gas turbine, computer software and a method for controlling an operating point of the gas turbine that includes a compressor, a combustor and at least a turbine is provided. The method comprises: determining an exhaust pressure at an exhaust of the turbine; measuring a compressor pressure discharge at the compressor; determining a turbine pressure ratio based on the exhaust pressure and the compressor pressure discharge; calculating a primary to lean-lean mode transfer threshold reference curve as a function of the turbine pressure ratio, where the primary to lean-lean mode transfer threshold curve includes points at which an operation of the gas turbine is changed between a primary mode to a lean-lean mode; and controlling the gas turbine to change between the primary mode and the lean-lean mode.

Apparatus for Releasing a Flow Cross Section of a Gas Line

An apparatus is described for the controlled release of a flow cross section of a gas line which is connected to a combustion chamber of a gas engine. The apparatus has a check valve and a flexible device. The flexible device is provided for absorbing a force occurring as a result of a thermal expansion of the check valve.

Fuel circuit for an aviation turbine engine, the circuit having a fuel pressure regulator valve

A fuel circuit for an aviation turbine engine, the fuel circuit including: a main fuel line for feeding fuel to a combustion chamber of the engine and including a positive displacement pump; an auxiliary fuel line connected to the main fuel line at a junction situated downstream from the pump and serving to feed fuel to hydraulic actuators to control variable-geometry equipment of the engine, the auxiliary fuel line including electrohydraulic servo-valves upstream from each actuator; and a fuel pressure regulator valve arranged on the main fuel line downstream from the pump.

AERO COMPRESSION COMBUSTION DRIVE ASSEMBLY CONTROL SYSTEM

A control system for an aero compression combustion drive assembly, the aero compression combustion drive assembly having an engine member, a transmission member and a propeller member, the control system including a sensor for sensing a pressure parameter in each of a plurality of compression chambers of the engine member, the sensor for providing the sensed pressure parameter to a control system device, the control system device having a plurality of control programs for effecting selected engine control and the control system device acting on the sensed pressure parameter to effect a control strategy in the engine member. A control method is further included. 1. A control method for an aero compression combustion drive assembly , the aero compression combustion drive assembly having an engine member , a transmission member and a propeller member , the control system comprising:sensing a pressure parameter in each of a plurality of compression chambers of the engine member;providing the sensed pressure parameter to a control system device;providing a plurality of control programs to the control system device; andthe control system device acting on the sensed pressure parameter to effect a control strategy in the engine member.2. The control method of claim 1 , including implementing the control strategy in the engine member by affecting the operation of at least one fuel injector.3. The control method of claim 2 , including affecting a fuel pulse timing of at least one fuel injector.4. The control method of claim 2 , including affecting a fuel pulse duration of at least one fuel injector.5. The control method of claim 2 , including affecting the operation of at least one turbocharger.6. A control method for an aero compression combustion drive assembly claim 2 , the aero compression combustion drive assembly having an engine member claim 2 , a transmission member and a propeller member claim 2 , the control system comprising:sensing a pressure parameter in each of ...

GAS TURBINE SYSTEM

Provided is a gas turbine including: a first compressor which compresses air; a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture; a combustor which combusts the generated fuel mixture from the mixer; a plurality of flow meters which adjusts an amount of the air or the fuel injected into the mixer; and a control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index rang. 1. A gas turbine system comprising:a first compressor which compresses air;a mixer which adds the compressed air from the first compressor to fuel and generates a fuel mixture;a combustor which combusts the generated fuel mixture from the mixer;a plurality of flow meter which adjust an amount of the air or the fuel injected into the mixer; anda control unit which maintains the Wobbe Index of the fuel mixture within a predetermined Wobbe Index range.2. The gas turbine system of claim 1 , wherein the first compressor compresses the air supplied from an external source.3. The gas turbine system of claim 1 , further comprising a second compressor which compresses the air supplied from an external source claim 1 , and supplies the compressed air from the second compressor to at least one of the combustor and the first compressor.4. The gas turbine system of claim 1 , wherein the plurality of flow meters comprise a fuel flow meter which adjusts an amount of the fuel supplied to the mixer.5. The gas turbine system of claim 4 , further comprising a first sensor unit which measures at least one of a temperature claim 4 , a pressure claim 4 , and a flux of fuel ejected from the fuel flow meter.6. The gas turbine system of claim 1 , further comprising a heat exchanger which heats at least one of the air ejected from the first compressor and the fuel supplied to the mixer.7. The gas turbine system of claim 6 , further comprising a turbine which operates by a combustion gas ejected from the combustor claim 6 ,wherein the heat ...

Fuel metering valve fail-fixed and back-up control system

A system provides “fail fixed” functionality and allows a user to manually manipulate fuel flow to a gas turbine engine in the unlikely event the primary control means is unavailable. The fuel metering unit includes a fuel metering valve, a flow increase valve, and a flow decrease valve. The flow increase valve and flow decrease valves are both in fluid communication with the fuel metering valve and are each adapted to selectively receive fuel flow commands from a primary fuel flow command source and from a secondary fuel flow command source. The flow increase and decrease valves are responsive to the fuel flow commands to selectively control the position of the fuel metering valve.

Gas fuel turbine engine for reduced oscillations

A gas fuel turbine engine may include a gaseous pilot fuel supply, a first main fuel supply, and a second main fuel supply. The first main fuel supply may provide gaseous fuel to a first plurality of fuel injectors, and the second main fuel supply may provide gaseous fuel to a second plurality of fuel injectors. The turbine engine may also include a flow restriction provided in the first main fuel supply. The second main fuel supply may be free of the flow restriction.

LIQUID FUEL ASSIST IGNITION SYSTEM OF A GAS TURBINE AND METHOD TO PROVIDE A FUEL/AIR MIXTURE TO A GAS TURBINE

A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase includes a high pressure tank, a vacuum pump connected to the high pressure tank, a liquid fuel inlet connected to the high pressure tank, an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine. 117-. (canceled)18. A liquid fuel assist ignition system for providing a fuel/air mixture to a gas turbine in its start-up phase , comprisinga high pressure tank,a vacuum pump connected to the high pressure tank,a liquid fuel inlet connected to the high pressure tank,an air inlet connected to the high pressure tank, and an outlet of the high pressure tank connected to a burner of the gas turbine.19. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an air pump connected to the air inlet for providing air to the high pressure tank.20. The liquid fuel assist ignition system according to claim 18 , wherein the vacuum pump and/or the liquid fuel inlet and/or the air inlet and/or the outlet and/or the pipes between the vacuum pump claim 18 , the liquid fuel inlet claim 18 , the air inlet and/or the outlet comprise(s) one or more control elements.21. The liquid fuel assist ignition system according to claim 20 , wherein the connection elements comprise switchable valves.22. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel inlet comprises a needle like pipe.23. The liquid fuel assist ignition system according to claim 18 , wherein the liquid fuel assist ignition system comprises an external heat source to heat up the high pressure tank.24. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source is an electric heater.25. The liquid fuel assist ignition system according to claim 23 , wherein the external heat source comprises a temperature controller and/or ...

Fuel metering system electrically servoed metering pump

A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.

Propulsion system for an aircraft

A hybrid-electric propulsion system includes a propulsor, a turbomachine, and an electrical system, the electrical system including an electric machine coupled to the turbomachine. A method for operating the propulsion system includes operating, by one or more computing devices, the turbomachine such that the turbomachine rotates the propulsor; receiving, by the one or more computing devices, a command to accelerate the turbomachine while operating the turbomachine; and providing, by the one or more computing devices, electrical power to the electric machine to add power to the turbomachine, the propulsor, or both in response to the received command to accelerate the turbomachine.

METHOD OF CONTROLLING A POSITION ACTUATION SYSTEM COMPONENT FOR A GAS TURBINE ENGINE

A method for controlling a position actuation system component in a gas turbine engine based on a modified proportional and integral control loop is provided. The method includes determining an error value between a demand signal for the position actuation system component and a position signal for the position actuation system component. The method also includes determining an integral gain scaler as a function of a scheduling parameter value and determining an integral gain based on the determined error value and the determined integral gain scaler. Additionally the method includes determining a proportional gain scaler as a function of the scheduling parameter value and determining a proportional gain based on the determined error value and the determined proportional portion gain scaler. The method adds the determined integral gain with the determined proportional gain to determine a null current value for the position actuation system component. 1. A method for controlling a position actuation system component in a gas turbine engine , the method comprising:determining an error value between a demand signal for the position actuation system component and a position signal of the position actuation system component;determining a scheduling parameter value of the gas turbine engine; anddetermining a null current value for the position actuation system component, wherein determining the null current value includesdetermining an integral gain scaler as a function of the scheduling parameter value;determining an integral gain based on the determined error value and the determined integral gain scaler;determining a proportional gain scaler as a function of the scheduling parameter value;determining a proportional gain based on the determined error value and determined proportional gain scaler; andadding the determined integral gain and the determined proportional gain to determine the null current value.2. The method of claim 1 , wherein the scheduling parameter is a ...

Metering Valve

A metering valve comprising a solenoid having: a coil mounted on a core; and an armature moveable axially with respect to the core and against a return bias in response to a current in the coil; a variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core. The metering valve comprises an electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor. A reference capacitor may be provided having opposing third and fourth plates at a set separation. A valve body may house the solenoid, the variable capacitor and the reference capacitor. 1. A metering valve comprising: a coil mounted on a core; and', 'an armature moveable axially with respect to the core and against a return bias in response to a current in the coil;, 'a solenoid havinga variable capacitor having a first plate mounted for movement with the armature and a second plate fixed with respect to the core; andan electronic feedback loop which is used to adjust the current in the coil based on a feedback signal derived from of the capacitance of the variable capacitor.2. The metering valve as claimed in claim 1 , further comprising:a reference capacitor having third and fourth plates at a set separation; anda valve body which houses the solenoid, the variable capacitor and the reference capacitor.3. The metering valve as claimed in claim 2 , further comprising a controller for controlling the current in the coil and the movement of the armature claim 2 , the controller being responsive to the feedback signal to adjust the current in the coil.4. The metering valve as claimed in claim 2 , wherein the electronic feedback loop is configured to:observe a ratio of the capacitances of the variable and reference capacitors; anduse the ratio of the capacitances to produce a feedback signal corresponding to a displacement of the armature.5. The metering valve ...

Modulating fuel for a turbine engine

A fuel supply system for a turbine engine that provides a modulated thrust control malfunction accommodation (TCMA). The fuel supply system can include a fuel line that fluidly connects a fuel tank and the turbine engine. A fuel pump and a fuel metering valve can be fluidly connected to the fuel line. A bypass line can fluidly connect to the fuel line. Flow through the bypass line can be controlled using a bypass valve and a balancing pressure valve. The TCMA can then modulate the fuel flow using the valves.

FEEDFORWARD CONTROL OF A FUEL SUPPLY CIRCUIT OF A TURBOMACHINE

A fuel supply system for a turbomachine, comprising a fuel circuit comprising pressurizer at the output of the circuit, a pump arranged to send into the circuit a fuel flow rate which is an increasing function of the rotational speed of a shaft of the pump, and a control circuit arranged to control the device to comply with a flow rate setpoint at the output of the fuel circuit. The system further comprises a feedforward corrector circuit configured to calculate an increment of the flow rate setpoint as a function of the engine speed of the turbomachine and of a variation in the engine speed of the turbomachine, and to add this increment to the flow rate setpoint. A method of regulating the pump is also described.

HYBRID GAS TURBINE ENGINE SYSTEM POWERED WARM-UP

An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state. 1. A hybrid gas turbine engine system of a hybrid electric aircraft , the hybrid gas turbine engine system comprising:a gas turbine engine comprising a low speed spool and a high speed spool;a generator operably coupled to the low speed spool of the gas turbine engine;a high spool electric motor operably coupled to the high speed spool; and monitor for a powered warm-up request;', 'initiate a powered warm-up state of the gas turbine engine based on detecting the powered warm-up request;', 'control the hybrid gas turbine engine system in the powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust; and', 'transition the gas turbine engine from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state., 'a controller configured to2. The hybrid gas turbine engine system of claim 1 , comprising one or more electric ...

Fuel Cutoff Testing System

A method and apparatus for controlling operation of an engine in an aircraft. A time when a cutoff speed for the aircraft will be reached at which a flow of fuel is to be stopped is identified. A delay between sending a command to move a switch to an off position and the time at which the engine ceases operation is also identified. The command is sent based on the predicted time and the delay. The command causes the switch to move to the off position moving a fuel control switch for the engine of the aircraft to a shut off position to stop the flow of fuel to the engine.

METERING DEVICE FOR A FUEL FEED CIRCUIT OF AN ENGINE

A metering device for an engine fuel feed circuit, the device including a metering valve, and a pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve, wherein the metering valve includes a seat provided with an inlet orifice and an outlet orifice, a shutter arranged within the seat, and an actuator controlling the position of the shutter, and wherein, between the inlet orifice and the outlet orifice the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position. 1. A metering device for an engine fuel feed circuit , the device comprising:a metering valve; anda pressure regulator device maintaining a constant pressure difference from downstream to upstream across the metering valve; a seat provided with an inlet orifice and an outlet orifice;', 'a shutter arranged within the seat; and', 'an actuator controlling the position of the shutter; and, 'wherein the metering valve compriseswherein, between the inlet orifice and the outlet orifice, the shutter defines a passage of minimum section that is variable as a function of the position of the shutter along a stroke extending between a bottom abutment and a top abutment and passing via a threshold position;{'b': '2', 'wherein the shutter is configured in such a manner that, firstly, the minimum section of said passage, and thus the flow rate of fuel passing through the valve, increases linearly as a function of the position coordinate of the shutter between the bottom abutment (b) and the threshold position, and that, secondly, the minimum section of said passage, and thus of the fuel flow rate, increases quadratically or more rapidly, as a function of the position coordinate of the shutter between the threshold position and the top abutment.'}2. A metering device according to claim 1 , wherein the ...

STATE DETERMINING DEVICE, OPERATION CONTROLLING DEVICE, GAS TURBINE, AND STATE DETERMINING METHOD

A state determining device determines a state of a gas turbine connected to an electric generator. The gas turbine includes a compressor that compresses intake air into compression air, a fuel supply device that supplies fuel, a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas, and a turbine that is rotated with the generated combustion gas. 1. A state determining device that determines a state of a gas turbine connected to an electric generator , the gas turbine comprising a compressor that compresses intake air into compression air , a fuel supply device that supplies fuel , a combustor that mixes the compression air supplied from the compressor and the fuel supplied from the fuel supply device and combusts a resultant mixture to generate combustion gas , and a turbine that is rotated with the generated combustion gas , the state determining device comprising:an instruction-value detecting unit that detects a difference in an instruction value related to an output of the gas turbine;an output detecting unit that detects a difference in an output of the electric generator; anda determining unit that determines an operation of the gas turbine has departed from a predetermined relation when a difference between the difference in the instruction value and the difference in the output is equal to or larger than a threshold.2. The state determining device according to claim 1 , wherein the instruction value is a fuel-flow instruction value of fuel to be supplied from the fuel supply device to the combustor.3. The state determining device according to claim 1 , whereinthe instruction-value detecting unit detects a difference between a detected instruction value and an instruction value detected at a last time, andthe output detecting unit detects a difference between a detected output and an output detected at a last time.4. An operation ...

MODEL BASED BUMP-LESS TRANSFER BETWEEN PASSIVE AND ACTIVE MODE OPERATION OF THREE-WAY CHECK VALVE FOR LIQUID FUEL DELIVERY IN GAS TURBINE SYSTEMS

A method using an inverse three-way valve model with feed-forward fuel flow control is provided for controlling liquid fuel flow in a turbine power generation system to achieve a bump-less driven watts (dwatt) power output during fuel mode transitions between passive mode and active mode operations of a three-way check valve that delivers liquid fuel to the turbine combustor nozzles. The method utilizes an inverse fluid flow model for a three-way check valve which is based upon a valve position surrogate for the three-way check valve to develop a calculated estimate of a fuel spike/dwatt oscillation likely to occur during mode transitions of the three-way check valve and to produce a feed-forward control used to modulate a fuel path bypass valve within the turbine fuel supply circulation system that provides the liquid fuel to the three-way valve during transfers of valve operation between passive and active mode operations. 1. A method for controlling liquid fuel flow to one or more three-way check valves used for delivering fuel to a turbine combustor in a turbine power generation system during transfers between passive and active modes of check valve operation , the turbine power generation system including a combustor fuel delivery three-way check valve and a bypass valve , the method comprising:producing a fuel flow spike estimation signal indicative of an inverse of a fuel flow spike occurring during mode transfers of a fuel delivery three-way check valve between passive and active modes;generating a bypass valve position command based on the fuel flow spike estimation signal; andproviding the bypass valve position command to the bypass valve during transfers between passive and active modes of check valve operation in a feed-forward control manner that counteracts or mitigates a fuel flow spike associated with such mode transfers.2. The method of wherein the fuel flow spike estimation signal is produced based on an inverse operational model of the three-way ...

COMBUSTION STAGING SYSTEM

A combustion staging system for fuel injectors of a multi-stage combustor of a gas turbine engine. The system includes plural fuel injectors, each having respective pilot and mains injection stages. It further includes a splitting unit which, to perform staging control of the combustor, receives a metered fuel flow and, for pilot and mains operation, controllably splits the received fuel flow into a pilot flow for injecting at the pilot stages of the injectors and a mains flow for injecting at the mains stages of the injectors, and for pilot-only operation, controllably splits the received fuel flow into a first part of the pilot flow for injecting at the pilot stages of a first portion of the injectors and a second part of the pilot flow for injecting at the pilot stages of a second portion of the injectors. 1. A combustion staging system for fuel injectors of a multi-stage combustor of a gas turbine engine , the combustion staging system including:plural fuel injectors, each having respective pilot and mains injection stages;a splitting unit (FSU) which, to perform staging control of the combustor, receives a metered fuel flow and, for pilot and mains operation, controllably splits the received fuel flow into a pilot flow for injecting at the pilot stages of the injectors and a mains flow for injecting at the mains stages of the injectors, and for pilot-only operation, controllably splits the received fuel flow into a first part of the pilot flow for injecting at the pilot stages of a first portion (Pilot 1) of the injectors and a second part of the pilot flow for injecting at the pilot stages of a second portion (Pilot 2) of the injectors; andpilot (Pilot) and mains (Mains) fuel manifolds distributing respective fuel flows from the splitting unit to the injectors;wherein each of the fuel injectors has a respective first solenoid valve which is movable between (i) a pilot-only operation position which shuts off the mains fuel manifold from the injector's mains ...

ECOLOGY FUEL RETURN SYSTEMS

A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine. 1. A shut-off valve comprising:a float configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G; anda negative G control component operatively connected to the float to limit fluid communication between a tank outlet and an ejector pump during negative G events.2. A shut-off valve as recited in claim 1 , wherein the negative G control component includes a biasing component claim 1 , wherein the biasing component is configured to apply a biasing force to the float claim 1 , wherein the biasing force is greater than a pre-determined negative G event force and less than the buoyancy force of the float at 1 G.3. A shut-off valve as recited in claim 2 , wherein in an occluded position the biasing force of the biasing component is greater or equal to the buoyancy force of the float at 1 G.4. A shut-off valve as recited in claim 2 , wherein in an unoccluded position the biasing force of the biasing component is less than the buoyancy force of the float at 1 G.5. A shut-off valve as recited in claim 2 , wherein the biasing component includes a spring operatively connected to a top portion of the float.6. A shut-off valve as ...

System and Method for Providing Highly Reactive Fuels to a Combustor

A system and related method for providing a highly reactive fuel to a combustor of a gas turbine are disclosed herein. The system includes a fuel supply system that is in fluid communication with a fuel supply. The fuel supply system includes multiple fuel circuits. Each fuel circuit individually feeds fuel to a corresponding fuel distribution manifold. The system further includes a steam injection system. The steam injection system includes at least one flow control valve that is in fluid communication with at least one of the fuel circuits. The flow control valve provides for fluid communication between a superheated steam source and the fuel circuit during both fueled operation and during non-fueled operation of the corresponding fuel circuit.

Device for controlling gas turbine, gas turbine facility, method for controlling gas turbine, and program for controlling gas turbine

A control device includes a load fuel quantity calculation unit, an allowable fuel quantity calculation unit, a flow rate low value selection unit, a basic drive quantity calculation unit, a fuel deviation calculation unit, and a correction unit. The load fuel quantity calculation unit determines a load fuel quantity based on a required output. The allowable fuel quantity calculation unit determines an allowable fuel quantity to protect a gas turbine. The flow rate low value selection unit selects a minimum fuel quantity from among the determined fuel quantities. The basic drive quantity calculation unit determines a basic drive quantity of an air intake quantity regulator. The fuel deviation calculation unit determines a fuel deviation between the allowable fuel quantity and the minimum fuel quantity. The correction value calculation unit determines a correction value corresponding to the fuel deviation which is then used to correct the basic drive quantity.

SYSTEM FOR PERFORMING STAGING CONTROL OF A MULTI-STAGE COMBUSTOR

A control system is provided for performing staging control of a multi-stage combustor of a gas turbine engine. The fuel is fed to the combustor by a fuel supply system comprising: a plurality of fuel manifolds distributing fuel to respective stages of the combustor, a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds, and an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds. The control system includes a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds. The control system further includes a controller which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split. 1. A fuel supply system for feeding fuel to a multi-stage combustor of a gas turbine engine , the fuel supply system comprising: a plurality of fuel manifolds which distribute fuel to respective stages of the combustor , a fuel metering valve operable to control the rate at which fuel passes to the fuel manifolds , an actuating arrangement which splits the fuel flow from the fuel metering valve between the fuel manifolds , and a control system for performing staging control of the combustor;wherein the control system includes:a fuel pressure sensor arrangement which senses the fuel pressure at entry to the actuating arrangement, and/or in one or more of the fuel manifolds; anda controller which commands the fuel metering valve to supply fuel to the combustor at a given flow rate, and which repeatedly: calculates a fuel split between the fuel manifolds based on the sensed fuel pressure(s), and issues a command signal to the actuating arrangement to implement the calculated fuel pressure-based fuel split.2. A fuel supply system according to claim 1 , wherein ...

ECOLOGY FUEL RETURN SYSTEMS

A shut-off valve includes a float and a negative G control component. The float is configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G. The negative G control component is operatively connected to the float to limit fluid, e.g. liquid or gas, communication between a tank outlet and an ejector pump during negative G events. An ecology fuel return system includes a tank, an ejector pump, a float, and a negative G control component, as described above. The tank has an inlet and an outlet. The inlet is configured to be in fluid communication with components of an engine. The ejector pump is in fluid communication with the tank outlet and is configured to pump fuel from the tank to a fuel pump inlet of an engine. 1. A shut-off valve comprising:a float configured to occlude a tank outlet at a first fluid level and 1 G and unocclude the tank outlet at a second fluid level and 1 G; anda negative G control component operatively connected to the float to limit fluid communication between a tank outlet and an ejector pump during negative G events.2. A shut-off valve as recited in claim 1 , wherein the negative G control component includes a slosh plate disposed proximate to the float surrounding at least a portion of the float claim 1 , wherein the slosh plate is configured to concentrate fluid between the slosh plate and the float during a negative G event to damp a displacement of the float against a negative G event force.3. A shut-off valve as recited in claim 2 , wherein a surface area of the slosh plate between a top of the float and the slosh plate is smaller than a collection area of the slosh plate.4. An ecology fuel return system claim 2 , comprising:a tank having an inlet and an outlet, wherein the inlet is configured to be in fluid communication with components of an engine for recovery of fuel;an ejector pump in fluid communication with the outlet of the tank, wherein the ejector pump is ...

METERING VALVE ASSEMBLY AND METHOD OF ASSEMBLY THEREOF

A valve assembly includes a body including an inlet port, an outlet port, and a flow passage extending therebetween. The flow passage includes a plurality of valve seats in a stepped arrangement between the inlet port and the outlet port. The valve assembly further includes a valve stem positioned within the flow passage. The valve stem includes at least one shaft and a poppet disk positioned at one end of the at least one shaft, and at least one reed petal coupled to the at least one shaft. The poppet disk is engageable with a first valve seat of the plurality of valve seats, and the at least one reed petal is engageable with a second valve seat of the plurality of valve seats. 1. A gas turbine engine system comprising:a combustor comprising a fuel nozzle; a body comprising an inlet port, an outlet port, and a flow passage extending therebetween and comprising a plurality of valve seats in a stepped arrangement between said inlet port and said outlet port; and', 'a valve stem positioned within said flow passage and comprising at least one shaft, a poppet disk positioned at one end of said at least one shaft, and at least one reed petal coupled to said at least one shaft, wherein said poppet disk is engageable with a first valve seat of said plurality of valve seats, and said at least one reed petal is engageable with a second valve seat of said plurality of valve seats., 'a valve assembly coupled in flow communication with said fuel nozzle, said valve assembly configured to channel a fluid from a fuel line to said fuel nozzle, said valve assembly comprising2. A system in accordance with claim 1 , wherein said valve stem further comprises a bias member configured to apply a force to said at least one shaft in a closing direction.3. The system in accordance with claim 1 , wherein said at least one reed petal comprises at least one aperture.4. The system in accordance with claim 1 , wherein said poppet disk and said at least one reed petal engages with said respective ...

FUEL SYSTEMS

A fuel system can include a total flow line configured to receive a total flow and a primary flow line connected to the total flow line. The primary flow line can be in fluid communication with one or more primary fuel nozzles of a nozzle assembly. The fuel system can include a secondary flow line connected to the total flow line in parallel with the primary flow line, the secondary flow line in fluid communication with a plurality of secondary flow nozzles of the nozzle assembly. The fuel system can include a flow split system configured to control a flow split between a primary flow of the primary flow line and a secondary flow of the secondary flow line. 1. A fuel system , comprising:a total flow line configured to receive a total flow;a primary flow line connected to the total flow line, the primary flow line in fluid communication with one or more primary fuel nozzles of a nozzle assembly;a secondary flow line connected to the total flow line in parallel with the primary flow line, the secondary flow line in fluid communication with a plurality of secondary flow nozzles of the nozzle assembly; anda flow split system configured to control a flow split between a primary flow of the primary flow line and a secondary flow of the secondary flow line.2. The fuel system of claim 1 , wherein the flow split system is configured to provide non-discrete flow splitting above a minimum flow split or at least a plurality of discreet flow splits above a minimum flow split.3. The fuel system of claim 2 , wherein the flow split system includes a secondary metering valve disposed on the secondary flow line and configured to be positioned to meter flow of the secondary flow line.4. The fuel system of claim 3 , further comprising a torque motor configured to operate the secondary metering valve to position the secondary metering valve to control the secondary flow of the secondary flow line.5. The fuel system of claim 4 , wherein the torque motor is a pressure servo valve ...

FUEL DELIVERY SYSTEM AND METHOD

A method of operating a fuel delivery system of an aircraft engine of an aircraft includes operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation, the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft, and no motive power to the aircraft, via the combustion of the trickle flow of fuel. An aircraft gas turbine engine is also described. 1. A method of operating a fuel delivery system of an aircraft engine of an aircraft , comprising operating the aircraft engine in a standby mode by maintaining combustion in a combustor of the aircraft engine by supplying fuel to the combustor via a first set of fuel nozzles of a first fuel manifold while providing a trickle flow of fuel via a second set of fuel nozzles of a second fuel manifold into the combustor during engine operation , the trickle flow being defined as a fuel flow rate selected to prevent flame-out of the combustion while providing one of: substantially no motive power to the aircraft , and no motive power to the aircraft , via the combustion of the trickle flow of fuel.2. The method of claim 1 , wherein the providing the trickle flow includes providing a trickle flow of fuel out of the second fuel manifold via a by-pass across a valve in the second fuel manifold.3. The method of claim 2 , wherein the providing the trickle flow includes providing a trickle flow of fuel out of the second fuel manifold via a by-pass across a valve in each of a plurality of fuel nozzles of the second fuel manifold.4. The method of claim 2 , wherein the providing the trickle flow includes providing a trickle flow of fuel to a location ...

SYSTEM AND METHOD FOR CONTROL OF GAS TURBINE ENGINE

Systems and methods for regulating fuel flow to a gas turbine engine are provided. Power for the engine is governed using a control structure having an inner control loop and an outer control loop, the outer control loop comprising a feedback controller that outputs a feedback command based on a power error determined as a function of a shaft horsepower, the feedback command used to determine a gas generator speed error, the gas generator speed error used by the inner control loop for outputting a fuel flow command. The shaft horsepower is determined from a torque measurement of the engine using a torque pressure transducer. When a momentary loss of the torque measurement from the torque pressure transducer is detected, power fluctuations due to the loss of torque measurement are limited by maintaining the feedback command from the feedback controller constant during the momentary loss of torque measurement. 1. A method of regulating fuel flow to a gas turbine engine , the method comprising:governing power for the engine using a control structure having an inner control loop and an outer control loop, the outer control loop comprising a feedback controller that outputs a feedback command based on a power error determined as a function of a shaft horsepower, the feedback command used to determine a gas generator speed error, the gas generator speed error used by the inner control loop for outputting a fuel flow command;determining the shaft horsepower from a torque measurement of the engine using a torque pressure transducer;detecting a momentary loss of the torque measurement from the torque pressure transducer; andlimiting power fluctuations due to the loss of torque measurement by maintaining the feedback command from the feedback controller constant during the momentary loss of torque measurement.2. The method of claim 1 , wherein detecting the momentary loss of the torque measurement comprises detecting a drop in a gearbox oil pressure of the engine.3. The ...

DEMAND FUEL SYSTEMS FOR TURBOMACHINES

A fuel system for a turbomachine includes a fuel tank and a first fuel line in fluid communication with the fuel tank and one or more fuel injectors. The first fuel line includes a main fuel pump disposed on the first fuel line, and an electric metering system disposed on the first fuel line downstream of the main fuel pump configured for starting the turbomachine and metering fuel to the fuel injectors. 1. A method for pumping fuel to a turbomachine , comprising:using an electric metering system to meter fuel to one or more fuel injectors of the turbomachine.2. The method of claim 1 , wherein the electric metering system is an electric pump configured to start the turbomachine and to meter fuel to the fuel injectors.3. The method of claim 1 , further comprising pumping fuel to the electric metering system using a mechanical vapor core fuel pump.4. The method of claim 1 , wherein the electric metering system includes a separate electric starter pump and a controllable metering valve.5. The method of claim 3 , further comprising flowing fuel to a fuel/oil cooler disposed downstream of the mechanical vapor core pump and the electric metering system.6. The method of claim 5 , wherein the fuel-oil cooler is between the electric metering system and the one or more fuel injectors.7. A method for not returning fuel to a fuel tank in a turbomachine to reduce heat addition to on-board fuel claim 5 , comprising:metering fuel to one or more fuel injectors of a turbomachine using an electric metering system to continuously pump only required fuel to the fuel injectors and thereby eliminating a need to return fuel to the fuel tank.8. The method of claim 7 , wherein the electric metering system is an electric pump configured to start the turbomachine and to meter fuel to the fuel injectors.9. The method of claim 7 , further comprising pumping fuel to the electric metering system using a mechanical vapor core fuel pump.10. The method of claim 7 , wherein the electric metering ...

Low emissions combustor assembly for gas turbine engine

A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.

Determination of a fuel delivery fault in a gas turbine engine

A method of determining a fuel delivery fault in a gas turbine engine is provided, the engine having a combustor, a combustor fuel system for delivering fuel to the combustor, and a turbine which is driven by hot gas from the combustor. The method includes comparing a measured turbine gas temperature profile against a predicted turbine gas temperature profile. The method further includes comparing a measured combustor instability against a predicted combustor instability. The method further includes indicating that a fuel delivery fault in the combustor fuel system has been detected when both the measured turbine gas temperature profile and the measured combustor instability differ from their predicted values by more than respective predetermined thresholds.

GAS TURBINE HEATER AND DUAL FUEL GAS TURBINE ENGINE

This disclosure teaches a gas turbine heater that can be used in either portable or stationary applications. In one embodiment, a gas turbine heater includes a gas turbine engine that generates hot exhaust gas, an air blower that draws an amount of air flow from ambient, a mixing plenum that allows the gas turbine exhaust and ambient air flow to mix together to create warm air, and an outlet that delivers the warm air to the customer. In another embodiment, a gas turbine heater includes a gas turbine engine that generates hot exhaust gas, an air blower that draws an amount of air flow from ambient, an air-to-air heat exchanger that transfers heat from the gas turbine exhaust to the ambient air flow to create warm air, and an outlet that delivers the warm air to the customer. 1. A direct-fired gas turbine heater comprising: a compressor that receives cold air at a compressor inlet and delivers compressed air at a compressor outlet;', 'a fuel manifold that receives combustible fuel at a fuel manifold inlet and delivers fuel at a fuel manifold outlet;', 'a combustor whose air inlet receives compressed air from the compressor outlet and whose fuel inlet receives fuel from the fuel manifold outlet, and whose igniter combusts the mixture of air and fuel inside the combustor, and delivers hot gas at a combustor outlet;', 'a turbine whose air inlet receives hot gas from the combustor outlet, and extracts energy from the hot gas as the hot gas flows through the turbine, and delivers hot gas at a turbine outlet;', 'a shaft that connects the compressor and turbine, such that the energy extracted by the turbine is used to drive the compressor;, 'a gas turbine engine comprisinga main air blower that receives cold air from ambient at a main air blower inlet and delivers cold air at a main air blower outlet;a mixing plenum having a cold air inlet that receives cold air from the main air blower outlet, a hot gas inlet that receives hot gas from the turbine, and a heater outlet that ...

AUXILLARY POWER UNIT ASSEMBLY AND A METHOD OF USING THE SAME

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

Pressure Sensor Noise Filter Prior to Surge Detection for a Gas Turbine Engine

A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of the FADEC channel A and the FADEC channel B to obtain a resultant value; a first comparator function to bound a proper high resultant value from the division function; a second comparator function to bound a proper low resultant value from the division function; and an OR gate in communication with the first comparator and the second comparator such that if an output from either the first comparator function and the second comparator function is true, that one of the FADEC channel A and the FADEC channel B is filtered out for a time period. 1. A filter algorithm for a dual channel electronic engine control system comprising:a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of said FADEC channel A and said FADEC channel B to obtain a resultant value;a first comparator function to bound a proper high resultant value from said division function;a second comparator function to bound a proper low resultant value from said division function; andan OR gate in communication with said first comparator and said second comparator such that if an output from either said first comparator function and said second comparator function is true, that one of said FADEC channel A and said FADEC channel B is filtered out for a time period.2. The assembly as recited in claim 1 , wherein said measured pressure rate of change is measured by a digital pressure sensor on each of said FADEC channel A and said FADEC channel B.3. The assembly as recited in claim 1 , wherein said digital pressure sensor on each of said FADEC channel A and said FADEC channel B is in communication with a fan section of a gas turbine ...

FREE GAS TURBINE WITH CONSTANT TEMPERATURE-CORRECTED GAS GENERATOR SPEED

A method of controlling a speed of a gas turbine engine, the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another, including determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine; controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; and controlling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool. 1. A method of controlling a speed of a gas turbine engine , the gas turbine engine including a high pressure spool and a low pressure spool rotating independently from one another , the method comprising:determining a temperature-corrected rotational speed of the high pressure spool based on an actual rotational speed of the high pressure spool and on an air temperature measured outside of the gas turbine engine;controlling the rotation of the high pressure spool to maintain the temperature-corrected rotational speed of the high pressure spool at least substantially constant throughout a range of a power demand on the gas turbine engine; andcontrolling a rotational speed of the low pressure spool independently of the rotation of the high pressure spool.2. The method as defined in claim 1 , wherein the temperature-corrected rotational speed of the high pressure spool is calculated as Ng/√{square root over (θ)} claim 1 , where Ng is the actual rotational speed of the high pressure spool and θ is the air temperature measured outside of the gas turbine engine.3. The method as defined in claim 1 , wherein the temperature-corrected rotational speed of the high pressure spool is maintained at least substantially constant by modulating ...

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON ACCELERATION POWER

Systems and methods for controlling an gas turbine engine are provided. The method comprises receiving a requested engine speed and obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow. A required fuel flow to obtain the requested engine speed is determined as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow. A command to a fuel flow metering valve is output in accordance with the required fuel flow. 1. A system for controlling a gas turbine engine , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed;', 'obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow; and', 'determining the required fuel flow to obtain the requested engine speed as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the required fuel flow based on an acceleration ...

SYSTEM AND METHOD FOR AN ENGINE CONTROLLER BASED ON INVERSE DYNAMICS OF THE ENGINE

Systems and methods for controlling a gas turbine engine are provided. The system comprises an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command and a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow. The controller comprises a feedforward controller configured for receiving a requested engine speed, obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed, and determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed. 1. A system for controlling a gas turbine engine of an aircraft , the system comprising:an interface to a fuel flow metering valve for controlling a fuel flow to the engine in response to a fuel flow command; and receiving a requested engine speed;', 'obtaining a steady-state fuel flow for the requested engine speed as a function of the requested engine speed, the steady-state fuel flow, and the relationship between fuel flow and gas generator speed; and', 'determining the required fuel flow to obtain the requested engine speed and the relationship between fuel flow and gas generator speed., 'a controller connected to the interface and configured for outputting the fuel flow command to the fuel flow metering valve in accordance with a required fuel flow, the controller comprising a feedforward controller configured for2. The system of claim 1 , wherein the controller is further configured to limit acceleration of the gas turbine engine by applying a rate limit to the requested engine speed.3. The system of claim 1 , wherein the controller comprises a feedback controller configured to adjust the required fuel flow based on an acceleration error.4. The system ...

SYSTEM AND METHOD FOR MONITORING FUEL ADDITIVES

A system for monitoring fuel additives on board a vehicle includes a fuel line carrying fuel from a fuel source to an engine; a fuel additive sensor configured to measure concentration of additives in fuel at a point along the fuel line; a fuel additive dispenser connected in parallel to the fuel line; at least one flow control device for controlling an amount of flow from the fuel line into the fuel additive dispenser; and a controller configured to receive input from the fuel additive sensor and to control the flow control device to adjust the amount of the flow from the fuel line into the fuel additive dispenser. 110-. (canceled)11. A method for monitoring fuel additives on board a vehicle , comprising:flowing fuel from a fuel tank along a fuel line to an engine;sensing concentration of additives in the fuel at a point along the fuel line;determining whether the concentration of the additive in the fuel is less than a fuel additive specification;when the concentration is less than the specification, operating a flow control device to divert a portion of the fuel from the fuel line along a parallel line to a fuel additive dispenser.12. The method of claim 11 , wherein the fuel additive dispenser is positioned along a fuel additive bypass line connected at an upstream end to the flow control device and connected at a downstream end back to the fuel line.13. The method of claim 12 , wherein the fuel additive sensor is positioned upstream of or at the flow control device.14. The method of claim 12 , wherein the fuel additive sensor is positioned downstream of the downstream end of the fuel additive bypass line.15. The method of claim 11 , wherein the controller is configured to compare the concentration with a pre-set additive requirement specification claim 11 , and to control the flow control device to increase flow through to fuel additive dispenser when the concentration is less than the specification.16. The method of claim 15 , wherein the controller is ...

Dual Schedule Flow Divider Valve, System, and Method for Use Therein

A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionally different split ratios dependent on ascending or descending combustion fuel flow is provided. The system includes a passive fuel divider valve (FDV) that includes a primary piston and a secondary piston. The primary piston is moveable independently from the secondary piston during a portion of its stroke, and is hydro-locked to the secondary piston during another portion of its stroke. An ecology valve is also provided to purge the fuel from the primary and/or secondary manifolds during different modes of operation. A transfer valve is included to control the position of ecology piston of the ecology valve. 1. A passive flow splitting system for use in a turbine engine fuel control system to provide split fuel flow to a primary fuel manifold and a secondary fuel manifold to supply primary fuel injectors and secondary fuel injectors , respectively , for particular combustion zones thereof , comprising:{'claim-text': ['a housing having an inlet, a primary manifold port, a secondary manifold port, and a plurality of flow paths;', 'a primary piston in communication with the inlet; and', 'a secondary piston,'], '#text': 'a passive fuel divider valve (FDV) configured to provide intentionally different split ratios dependent on ascending or descending fuel mass flow rate, the FDV including:'}wherein the primary piston is moveable independently of the secondary piston to meter fuel flow from the primary manifold port to the primary manifold of the turbine engine fuel control system, and being biased away from the secondary piston,wherein the secondary piston is configured to meter fuel flow from the secondary manifold port to the secondary manifold of the turbine engine fuel control system, and being biased to prohibit the fuel flow from ...

COMBINED HEAT AND POWER SYSTEM AND METHOD OF OPERATION

A combined heat and power system and method of operation is provided. The system includes a combustion chamber configured to directly combust solid organic material. A compressor turbine is fluidly coupled to the combustion chamber. An expansion turbine is fluidly coupled to the combustion chamber. In an embodiment, the system has a low turbine pressure ratio. 1. A combined heat and power system comprising:a combustion chamber configured to directly combust solid organic material;a compressor turbine fluidly coupled to the combustion chamber; andan expansion turbine fluidly coupled to the combustion chamber,wherein a turbine pressure ratio is less than 8.2. The system of claim 1 , wherein the turbine pressure ratio is less than 4.3. The system of claim 1 , further comprising a uni-flow cyclone fluidly coupled between the combustion chamber and the expansion turbine.4. The system of claim 1 , further comprising a generator operably coupled to the expansion turbine.5. The system of claim 3 , further comprising a fuel feed system fluidly coupled to the combustion chamber claim 3 , the fuel feed system having a hopper configured to receive the solid organic material and a feed tube disposed between the hopper and the combustion chamber.6. The system of claim 5 , further comprising a metering device disposed between the hopper and the feed tube claim 5 , the metering device being configured to selectively flow pressurized gas from the combustion chamber to the hopper.7. The system of claim 6 , wherein the hopper is sized to provide fuel to the combustion chamber for 1 to 6 hours of operation.8. The system of claim 7 , further comprising an ash bin operably coupled to the uni-flow cyclone and fluidly coupled to the hopper by a flow control valve claim 7 , wherein the flow control valve is configured to flow pressurized air from the hopper to the ash bin prior to the hopper being refilled with solid organic fuel.9. The system of claim 1 , further comprising a second cycle ...

Fuel meter protected from icing

A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

METERING VALVE ASSEMBLY AND METHOD OF ASSEMBLY THEREOF

A valve assembly includes a body including an inlet port, an outlet port, and a flow passage extending therebetween. The flow passage includes a plurality of valve seats in a stepped arrangement between the inlet port and the outlet port. The valve assembly further includes a valve stem positioned within the flow passage. The valve stem includes at least one shaft and a poppet disk positioned at one end of the at least one shaft, and at least one reed petal coupled to the at least one shaft. The poppet disk is engageable with a first valve seat of the plurality of valve seats, and the at least one reed petal is engageable with a second valve seat of the plurality of valve seats. 1. A valve assembly comprising:a body comprising an inlet port, an outlet port, and a flow passage extending therebetween and comprising a plurality of valve seats in a stepped arrangement between said inlet port and said outlet port; anda valve stem positioned within said flow passage and comprising at least one shaft, a poppet disk positioned at one end of said at least one shaft, and at least one reed petal coupled to said at least one shaft, wherein said poppet disk is engageable with a first valve seat of said plurality of valve seats, and said at least one reed petal is engageable with a second valve seat of said plurality of valve seats.2. The valve assembly in accordance with claim 1 , wherein said valve stem further comprises a bias member configured to apply a force to said at least one shaft in a closing direction.3. The valve assembly in accordance with claim 1 , wherein said poppet disk and said at least one reed petal engages with said respective valve seat of said plurality of valve seats in a closed valve position.4. The valve assembly in accordance with claim 1 , wherein said valve stem is configured to progressively unseat from said body during valve opening.5. The valve assembly in accordance with claim 1 , wherein said at least one reed petal comprises at least one ...

Gas turbine combustor control system

In one embodiment, a gas turbine system includes a controller configured to receive fuel composition information related to a fuel used for combustion in a turbine combustor; receive oxidant composition information related to an oxidant used for combustion in the turbine combustor; receive oxidant flow information related to a flow of the oxidant to the turbine combustor; determine a stoichiometric fuel-to-oxidant ratio based at least on the fuel composition information and the oxidant composition information; and generate a control signal for input to a fuel flow control system configured to control a flow of the fuel to the turbine combustor based on the oxidant flow information, a target equivalence ratio, and the stoichiometric fuel-to-oxidant ratio to enable combustion at the target equivalence ratio in the presence of an exhaust diluent within the turbine combustor.

FUEL METERING VALVE SYSTEM

A fuel metering valve system for use with a flow of fuel in a gas turbine engine may include a number of orifice plate lines, a number of differently sized orifice plates, and a number of orifice plate line valves. One of the orifice plate line valves opens and closes one of the orifice plates on the orifice plate lines. 1. A fuel metering valve system for use with a flow of fuel in a gas turbine engine , comprising:a plurality of orifice plate lines;a plurality of differently sized orifice plates; anda plurality of orifice plate line valves;wherein one of the plurality of orifice plate line valves opens and closes one of the plurality of orifice plates on the plurality of orifice plate lines.2. The fuel metering valve system of claim 1 , further comprising an inlet manifold in communication with the plurality of orifice plate lines.3. The fuel metering valve system of claim 1 , further comprising an upstream pressure-temperature sensor upstream of the plurality of orifice plate lines.4. The fuel metering valve system of claim 1 , further comprising an outlet manifold in communication with the plurality of orifice plate lines.5. The fuel metering valve system of claim 1 , further comprising a downstream pressure-temperature sensor downstream of the plurality of orifice plate lines.6. The fuel metering valve system of claim 1 , wherein the plurality of differently sized orifice plates comprises a parallel arrangement.7. The fuel metering valve system of claim 1 , wherein the plurality of orifice plate line valves comprises a plurality of solenoid valves.8. The fuel metering valve system of claim 1 , wherein the plurality of orifice plate line valves comprises a plurality of on and off valves.9. The fuel metering valve system of claim 1 , further comprising a flow controller in communication with the plurality of orifice plate line valves.10. The fuel metering valve system of claim 1 , wherein a first of the plurality of differently sized orifice plates comprises a ...

ENGINE ASSEMBLY AND METHOD OF OPERATION

A power plant assembly, including a turbine for driving at least one rotor shaft; a combustion chamber for generating drive energy for the turbine; at least one electric machine which is coupled to the rotor shaft and can be operated both in a generator mode and in a motor mode; and at least one energy storage system which is connected to the electric machine and can store energy generated by the electric machine when the electric machine is in generator mode. A set of control electronics of the power plant assembly is configured to operate the combustion chamber using a lean fuel-air mixture and, for this purpose, to selectively operate the at least one electric machine in generator mode or in motor mode, depending on the power to be applied by the power plant assembly.

OPTIMAL FEEDBACK HEAT ENERGY INTERNAL COMBUSTION ENGINE AND APPLICATIONS

An internal combustion engine wherein a thermo potential heat flow in combustion is maximized by providing a feedback of an optimized amount of thermo potential heat flow that is modulated in the exhaust media, into the air intake, and a method of providing feedback comprises producing a shock wave of pulse of exhaust media and pulse of intake air on the opposite side of a high temperature shock tube thereby transferring the thermo potential heat energy flow from the exhaust media to the air intake. 1. An optimal heat energy feedback engine comprising:a shockwave mechanism configured to trigger a shock wave effect and exchange heat energy of media and air to raise the output of heat energy from media; a fuel supply tube that contains a mechanism to establish adequate fuel pressure to trigger shock wave effect;', 'an air supply tube that contains a mechanism to establish adequate air pressure to trigger shock wave effect;', a closed position in which the fuel mixture with pressure from the fuel supply tube is separated from the air with pressure from the air supply tube; and', 'an open position in which the fuel and air suddenly mix to form a combustion air shockwave; and, 'a stationary space with a separating plate operable between a closed position and an open position, wherein the separating plate is configurable between, 'an air buffer zone in fluid communication with an opening of the stationary space and configured to collect the shock wave air from the stationary space;, 'wherein the shockwave mechanism comprisesa combustion chamber in fluid communication with the shockwave mechanism configured to receive the media from the shockwave mechanism and to mix the media with fuel and air to facilitate complete combustion of the fuel to produce hot air with higher energy efficiency;wherein the combustion chamber comprises:a second fuel supply tube that contains a mechanism to establish adequate pressure to achieve complete combustion in the combustion chamber when ...

GAS TURBINE PLANT WITH EXHAUST GAS RECIRCULATION AND ALSO METHOD FOR OPERATING SUCH A PLANT

A gas turbine plant is provided with exhaust gas recirculation and includes a main gas turbine having a main compressor and main turbine driving a main generator, and a combustion chamber, with an outlet connected to the inlet of the main gas turbine, has a fuel feed, and via the recuperator's high-pressure side obtains combustion air from the main gas turbine's compressor outlet. The outlet of the main turbine and the inlet of the main compressor are connected via the recuperator's low-pressure side and a cooler for exhaust gas recirculation. On the recuperator's low-pressure side, a charging unit, with a compressor and a turbine is arranged, and draws in air via an air intake and by the outlet of its compressor is connected to the recuperator's low-pressure side outlet and by the inlet of its turbine is connected to a surplus-gas extraction line on the recuperator's low-pressure side. 1. A method for operating a gas turbine plant in a partially closed , charged gas turbine cycle , the method comprising:combusting fuel in a combustion chamber, feeding a gaseous compressed operating medium which contains combustion air;expanding the operating medium, which contains hot combustion gases, in a main turbine of a main gas turbine, thereby performing work;extracting heat from the operating medium in a subsequent recuperator and in a cooler;compressing the operating medium in a compressor of the main gas turbine, and heat is fed to the compressed operating medium in the recuperator before re-entry into the combustion chamber;extracting on the low-pressure side of the recuperator a partial flow of the operating medium at an extraction point which is at a suitable first temperature level, and further expanded in a turbine of a charging unit; drawing in and compressing air by a compressor of the charging unit; andfeeding the air to the operating medium on a low-pressure side of the recuperator.2. The method as claimed in claim 1 , wherein COis separated from recirculated ...

Breaker auto-synchronizer

A breaker between two electrical circuits is provided that is closed when electrical properties in both of the electrical circuits are matching. Two check circuits are provided for comparing electrical properties of the two electrical circuits. Each of the check circuits sets a corresponding authorization to close the breaker. The breaker is only closed if both check circuits set an authorization to close the circuit.

ENERGY WEAPON HAVING A FAST START TURBINE FOR A HIGH POWER GENERATOR

A system platform includes a gas turbine engine coupled to a high power generator. The high power generator, driven by the gas turbine engine, supplies power to high power subsystems of the platform. 1. A weapon system platform comprisinga high-energy beam unit configured to discharge high-energy beams,a gas turbine engine configured to provide power for the high-energy beam unit, the gas turbine engine including a first shaft coupled to a compressor and a high pressure turbine rotor, a second shaft concentric with and independently rotatable relative to the first shaft and coupled to a low pressure turbine rotor, a starter adapted to rotate the first shaft, and a combustor adapted to combine air received from the compressor with fuel and to burn the fuel to supply high pressure gasses toward the high pressure turbine rotor and low pressure turbine rotor to rotate the first and second shafts,a generator coupled to the second shaft of the gas turbine engine and adapted to generate electricity when driven by the gas turbine engine,an energy storage unit coupled to the generator and configured to store the electricity generated by the generator, anda generator control system configured to selectively operate the starter and to selectively deliver fuel to the combustor such that the first shaft is continuously rotated by at least one of the starter and high pressure gasses from the combustor and the second shaft is selectively rotated by high pressure gasses from the combustor.2. The system platform of claim 1 , wherein fuel is selectively delivered to the combustor when an amount of electricity stored in the energy storage unit is below a threshold level.3. The system platform of claim 1 , wherein fuel is selectively delivered to the combustor when a power demand signal is received by the generator control system.4. The system platform of claim 1 , further comprising a load shaft gearbox coupled to the second shaft and the generator claim 1 , wherein the load shaft ...

Hazgas system with acoustic wave sensors

A gas monitoring system for monitoring gas leaks from a gas turbine engine disposed within a gas turbine enclosure includes a controller including a processor and a memory communicatively coupled to the processor. The memory stores instructions which when executed by the processor perform operations including obtaining one or more operational parameters associated with a gas turbine system having the gas turbine engine from one or more sensors during operation of the gas turbine engine. The operations also include utilizing a gas leakage monitoring model to monitor for gas leaks within the gas turbine enclosure and to generate a gas index indicative of a severity of a gas leak within the gas turbine enclosure based on the one or more operational parameters. The operations further include outputting the index.

HYBRID GAS TURBOFAN POWERED SUB-IDLE DESCENT MODE

A method of operating an aircraft hybrid gas turbofan during an idle mode of operation includes reducing a fuel flow to a primary gas turbine engine and boosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines, such that a net fuel reduction is achieved. The net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine. 1. A method of operating an aircraft hybrid gas turbofan during an idle mode of operation of a primary gas turbine engine , the method comprising:reducing a fuel flow to the primary gas turbine engine; andboosting a high spool of the primary gas turbine engine using a secondary gas turbine engine via a first power linkage connecting the primary and secondary gas turbine engines such that a net fuel reduction is achieved,wherein the net fuel reduction accounts for fuel flow to the primary gas turbine engine and fuel flow to the secondary gas turbine engine.2. The method of claim 1 , wherein the primary gas turbine engine is a propulsion engine and the secondary gas turbine engine is an auxiliary power unit (APU).3. The method of claim 1 , wherein boosting the high spool of the primary gas turbine engine comprises:driving a generator with the secondary gas turbine engine;coupling a motor to the high spool; andpowering the motor via the generator.4. The method of claim 1 , wherein boosting the high spool of the primary gas turbine engine comprises:generating compressed air with the secondary gas turbine engine; andproviding the compressed air directly into a turbine of the high spool of the primary gas turbine engine to provide high spool torque.5. The method of claim 1 , wherein boosting the high spool of the primary gas turbine engine comprises:driving a generator with the second engine;coupling a motor to the high spool;powering the motor via the generator;generating ...

HYBRID GAS TURBINE ENGINE SYSTEM POWERED WARM-UP

An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine, an electric motor operable to perform an electric taxiing of the hybrid electric aircraft, and a controller. The controller is operable to prevent fuel flow to the gas turbine engine during at least a portion of the electric taxiing and monitor for a powered warm-up request during the electric taxiing. A powered warm-up state of the gas turbine engine is initiated based on detecting the powered warm-up request. The powered warm-up state adds heat to one or more components of the gas turbine engine prior to transitioning to a takeoff power state. The gas turbine engine transitions from the powered warm-up state to the takeoff power state after reaching a target temperature of the one or more components in the powered warm-up state. 1. A hybrid gas turbine engine system of a hybrid electric aircraft , the hybrid gas turbine engine system comprising:a gas turbine engine;an electric motor operable to perform an electric taxiing of the hybrid electric aircraft; and prevent fuel flow to the gas turbine engine during at least a portion of the electric taxiing;', 'monitor for a powered warm-up request during the electric taxiing;', 'initiate a powered warm-up state of the gas turbine engine based on detecting the powered warm-up request, wherein the powered warm-up state adds heat to one or more components of the gas turbine engine prior to transitioning to a takeoff power state; and', 'transition the gas turbine engine from the powered warm-up state to the takeoff power state after reaching a target temperature of the one or more components in the powered warm-up state., 'a controller operable to2. The hybrid gas turbine engine system of claim 1 , wherein the powered warm-up state comprises enabling one or more electric heaters.3. The hybrid gas turbine engine system of claim 1 , wherein the gas turbine engine comprises a ...

METHODS AND SYSTEMS FOR STARTING A GAS TURBINE ENGINE

Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine. 1. A method of starting a gas turbine engine , comprising:monitoring, during startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine;detecting a low-pressure event for the primary fuel supply when the fuel pressure falls below a predetermined threshold; andresponsive to detecting the low pressure event, activating, by an engine controller, an electric backup boost pump to provide fuel to the gas turbine engine.2. The method of claim 1 , wherein monitoring the fuel pressure is performed responsive to detecting a flameout event for the gas turbine engine.3. The method of claim 2 , further comprising arming the electric backup boost pump responsive to detecting the flameout event and prior to detecting the low pressure event.4. The method of claim 1 , wherein detecting the low pressure event comprises:comparing a plurality of first pressure readings to the predetermined pressure threshold; anddetecting the low pressure event when at least two of the plurality of first pressure readings are below the predetermined pressure threshold.5. The method of claim 1 , further comprisingdeactivating the electric backup boost bump after a predetermined time delay;detecting one or more subsequent low pressure events for the primary fuel supply; andresponsive to detecting the one or more subsequent low pressure events, reactivating, by the engine controller, the electric backup boost pump to provide fuel to the gas turbine engine.6. The method of claim 1 , further comprising:obtaining a request to ...

GAS TURBOMACHINE FUEL SYSTEM, CONTROL SYSTEM AND RELATED GAS TURBOMACHINE

Various embodiments include gas turbomachine (GT) fuel systems, related control systems and GTs. In some cases, the GT fuel system includes: a plurality of combustion chambers circumferentially disposed around a gas turbine; a set of fuel nozzles directly mounted to each of the plurality of combustion chambers; a set of conduits coupled with each of the set of fuel nozzles at a first end of each of the conduits; and a set of liquid fuel check valves coupled with a second end of each of the set of conduits, the set of liquid fuel check valves being positioned radially offset and axially offset from the set of fuel nozzles. 1. A gas turbomachine fuel system comprising:a plurality of combustion chambers circumferentially disposed around a gas turbine;a set of fuel nozzles directly mounted to each of the plurality of combustion chambers;a set of conduits coupled with each of the set of fuel nozzles at a first end of each of the conduits; anda set of liquid fuel check valves coupled with a second end of each of the set of conduits, the set of liquid fuel check valves being positioned radially offset and axially offset from the set of fuel nozzles.2. The gas turbomachine fuel system of claim 1 , wherein the set of liquid fuel check valves are circumferentially disposed around the gas turbine.3. The gas turbomachine fuel system of claim 1 , wherein the set of fuel nozzles are located adjacent each of the plurality of combustion chambers.4. The gas turbomachine fuel system of claim 3 , wherein the set of liquid fuel check valves are located at a greater axial distance and a greater radial distance from each combustion chamber than the set of fuel nozzles.5. The gas turbomachine fuel system of claim 1 , wherein the set of conduits spans an axial-radial path between the set of fuel nozzles and the set of liquid fuel check valves.6. The gas turbomachine fuel system of claim 1 , wherein a distance of the radial offset between the set of liquid fuel check valves and the set of ...

METHOD FOR SELECTION OF OPTIMAL ENGINE OPERATING CONDITIONS FOR GENERATING LINEARIZED MODELS FOR ON-BOARD CONTROL AND ESTIMATION

A system for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine includes a memory configured to store a model of the gas turbine engine. The system also includes a model generation processor coupled to the memory and designed to perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope, divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters, select multiple combinations of base points within each of the multiple regions, perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions, and select final base points from the multiple combinations of base points based on the accuracy. 1. A system for generating a base point database for use by a full authority digital engine control (FADEC) to control a gas turbine engine during flight , the system comprising:a memory configured to store a model of the gas turbine engine; and perform an initial simulation of the gas turbine engine using the model to determine ranges of sensitivity of desired engine parameters throughout an operating envelope,', 'divide the operating envelope into a multiple regions based on the ranges of sensitivity of the desired engine parameters,', 'select multiple combinations of base points within each of the multiple regions,', 'perform an additional simulation of the gas turbine engine to determine an accuracy of interpolation between each of the multiple combinations of base points for each of the multiple regions, and', 'select final base points from the multiple combinations of base points based on the accuracy., 'a model generation processor coupled to the memory and configured to2. The system of claim 1 , wherein the ...

System and method to control a gas turbine subject to fuel composition variation

A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method also includes operating a second effector to maintain operation of the first effector within a first boundary limit, the second effector operation being initiated when the operating the first effector reaches a second boundary limit within the first boundary limit.

A method and a device for generating a command for the flow rate of fuel that is to be injected into a combustion chamber of a turbine engine

During a stage (E 0 ) of starting the turbine engine, the method of the invention comprises: an open-loop generating step (E 10 ) of generating a fuel flow rate command (WF_OL) from at least one pre-established relationship; and a closed-loop monitoring step (E 20 -E 30 ) of monitoring at least one operating parameter of the turbine engine selected from: a rate of acceleration (dN 2 /dt) of a compressor of the turbine engine; and a temperature (EGT) at the outlet from a turbine of the turbine engine; this monitoring step comprising maintaining (E 30 ) the operating parameter in a determined range of values by using at least one corrector network (R 1 , R 2 , R 3 ) associated with the parameter and suitable for delivering a signal for correcting the open-loop generated fuel flow rate command so as to maintain the operating parameter in the determined range of values.

FUEL METERING UNIT FOR TURBINE ENGINE

The invention relates to a fuel metering and distribution unit () which comprises in particular a slide valve () and a set of slots () configured with geometries, dimensions and positions such that: 1. A fuel metering and distribution unit , capable of controlling the fuel feed of a start-up injection ramp and of a main injection ramp in a combustion chamber of a turbine engine , a movable slide valve,', 'a feed port for the fuel flow rate to be distributed at least between the start-upstart-up injection ramp and the main injection ramp,', 'a first outlet port feeding the start-upstart-up ramp through a flow area on a span of the slide valve,', 'a regulator regulating the pressure differential between this outlet port and the feed port, so as to obtain, at the flow area, a metered total flow rate that is a function of a control current,', 'a second outlet port feeding the main ramp,, 'including a multi-outlet metering device comprising in a sleevewherein the second outlet port is fed through a set of slots, said set of slots being situated on a span of the slide valve other than that where said flow area of the outlet port feeding the start-upstart-up ramp is situated, and being fed by the first outlet port feeding the start-upstart-up ramp, the second outlet port thus being able to receive a portion of the total metered flow rate,said set of slots being more or less open depending on the position of the slide valve, so that the flow area defined by said set of slots varies and the distribution of flow rate between the start-upstart-up ramp and the main ramp varies as a function of the control current, in a first range of displacement of the slide valve, the flow area which feeds the first outlet port of the start-upstart-up ramp is progressively opened with the displacement of the slide valve, while the area of the set of slots which feeds the second outlet port of the main ramp is closed,', 'then, in a second range of displacement of the slide valve, the area of ...

Feed Forward Load Sensing For Hybrid Electric Systems

Hybrid electric systems and methods therefore are provided. In one exemplary aspect, a hybrid electric system includes an engine, an electric machine operatively coupled thereto and configured to generate electrical power when driven by the engine. One or more electrical loads are electrically connectable with the electric machine. An engine controller of the engine receives load state data indicative of electrical loads that anticipate electrically disconnecting from or electrically connecting to the electric machine at a predetermined time. In this way, the engine controller can anticipate electrical load changes and the engine can be controlled to adjust its torque output in anticipation of the electrical load change. In another exemplary aspect, a hybrid electric system is provided that includes features for nearly instantaneously reacting to load changes on the engine based on load state data received from feed forward inputs of the electrical system of the hybrid electric system. 1. A hybrid electric system , comprising:an engine configured to generate a torque output;an electric machine operatively coupled with the engine and configured to generate electrical power when driven by the engine;one or more electrical loads selectively electrically connectable with the electric machine and configured to receive electrical power from the electric machine when electrically connected thereto; receive load state data associated with the one or more electrical loads;', 'determine, based on the load state data, whether a load change on the engine is anticipated; and', 'generate a control command based at least in part on whether the load change on the engine is anticipated., 'an engine controller configured to control the engine and communicatively coupled with the one or more electrical loads, the engine controller configured to2. The hybrid electric system of claim 1 , wherein the control command is representative of instructions for changing the torque output of the ...

Piezoelectric Ring Bender Servo Valve Assembly For Aircraft Flight Control Actuation And Fuel Control Systems

A piezoelectric ring bender servo valve assembly reduces mechanical wear by removing mechanical components used in prior art servo valves. The assembly does not use torque motor, flapper, and feedback spring. In this manner, no moving parts are required, which reduces maintenance and costs. A pair of piezoelectric ring benders mount adjacently to a pair of nozzles. The piezoelectric ring benders independently regulate the flow of fluid through the nozzles by moving between an open position to enable flowage, and a closed position to restrict flowage. A linear position sensing device measures and provides feedback about the spool position to a valve controller. The valve controller allows the spool valve to move until valve position achieves command position and the force on the spool valve is in equilibrium with pressure difference across spool valve. An H-bridge operable to switch the polarity of a differential pressure applied across to a load. 1. A piezoelectric ring bender servo valve assembly , the assembly comprising:a valve housing, the valve housing being defined by a passageway, the passageway being operable to carry a fluid;a pair of nozzles, the nozzles being in communication with the fluid, the nozzles terminating at a pair of orifices;a pair of piezoelectric bendable members disposed adjacent to the nozzles, the piezoelectric bendable members being operable to bend to an open position away from the nozzles to enable flowage of the fluid through the nozzles, the piezoelectric bendable members being operable to return to a closed position towards the nozzles to at least partially restrict flow through the nozzles;a spool valve operationally connected to the piezoelectric bendable members, the spool valve being disposed in at least one spool position to regulate flow of the fluid through the passageway, the piezoelectric bendable members controlling operation of the spool position;a variable restrictor operatively connected to the nozzles, the variable ...

Controller and method

A controller for a gas turbine is arranged to supply a load L. The gas turbine includes a fuel supply arranged to supply fuel at a fuel flow rate FF to a combustor, wherein the fuel supply includes a first fuel supply and a second fuel supply. The controller is arranged to determine one or more ratios R of one or more combustor operating parameters COP respectively at the load L to respective reference combustor operating parameters COPR at a reference load LR. The controller is further arranged to control a proportion P of the fuel flow rate FF supplied via the first fuel supply based, at least in part, on the determined one or more ratios R. A gas turbine with the controller and a method controls the gas turbine.

Method and system for augmenting the detection reliability of secondary flame detectors in a gas turbine

Systems and methods for operating a gas turbine combustion system by generating a flame detection signal are provided. A set of modeled parameters expected when there is a flame in a secondary combustion zone is calculated. A set of measured gas turbine parameters is measured. A flame validation signal based on the set of measured parameters and the set of modeled parameters is generated. The systems include a subsystem that calculates a set of modeled parameters expected when there is a flame in the secondary combustion zone and a subsystem that measures a set of measured parameters. A subsystem generates a flame validation signal based on the set of measured parameters and the set of modeled parameters.

SYSTEM AND METHOD FOR OPERATING A GAS TURBINE IN A TURNDOWN MODE

A system for operating a thermal power plant during off-peak demand intervals includes a gas turbine having a compressor, a combustor connected to a fuel control system, a turbine and a sensor configured to sense ambient conditions around the gas turbine. The fuel control system and the sensor are in communication with a controller. The controller is configured to receive a user input that corresponds to a value for an operational boundary condition of the thermal power plant and to monitor ambient conditions through the sensor. The controller is further configured to generate a predicted emissions level value for the gas turbine based on the monitored ambient conditions and to generate a command signal to adjust at least one operational parameter of the gas turbine based at least in part on the predicted emissions level value and the value of the operational boundary condition of the thermal power plant. 1. A system for operating a gas turbine of a thermal power plant during turndown intervals , the system comprising:a. a gas turbine having a compressor, at least one combustor downstream from the compressor and a turbine downstream from the combustor, the combustor being connected to a fuel supply control system; andb. a sensor disposed within the thermal power plant; i. receive a user input corresponding to a value for an operational boundary condition of the thermal power plant;', 'ii. monitor ambient conditions using the sensor;', 'iii. generate a predicted emissions level value for the gas turbine based on the monitored ambient conditions; and', 'iv. generate a command signal to adjust at least one operational parameter of the gas turbine, the command signal being based at least in part on the predicted emissions level value and the value of the operational boundary condition of the thermal power plant., 'c. a controller in communication with the sensor and the fuel supply control system, the controller being configured to2. The system as in claim 1 , wherein ...

DUAL FUEL GAS TURBINE THRUST AND POWER CONTROL

An aircraft, controller, and method for simultaneously using a liquid fuel and a gaseous fuel. The use of natural gas and other similar fuels in gas turbines engines can enable an aircraft to operate less expensively. However, aircraft often use liquid fuels en route to the gas turbine engine burners for secondary purposes, such as oil cooling and hydraulic pressure. The aircraft, controllers, and methods described herein feed a minimal quantity of liquid fuel to an engine to satisfy the secondary purposes while simultaneously feeding a quantity of gaseous fuel to the engine to satisfy a thrust command for the engine. 1. An aircraft , comprising:a first fuel storage container configured to store a liquid fuel;a second fuel storage container configured to store a gaseous fuel;a gas turbine engine that includes fuel nozzles configured to inject the liquid fuel and the gaseous fuel into a burner of the gas turbine engine; anda controller configured to simultaneously meter flow of both the liquid fuel and the gaseous fuel to the fuel nozzles from the first fuel storage container and the second fuel storage container, wherein the controller is configured to meter the flow of the liquid fuel to satisfy an operating limit of the gas turbine engine.2. The aircraft of claim 1 , further comprising a selectable switch in communication with the controller claim 1 , wherein the controller does not permit flow of the gaseous fuel when the switch is in a first position claim 1 , and wherein the controller permits flow of the gaseous fuel when the switch is in a second position.3. The aircraft of claim 2 , wherein the switch automatically switches to the second position when the aircraft is configured for cruise flight.4. The aircraft of claim 1 , further comprising a throttle control in communication with the controller claim 1 , wherein the throttle control provides a thrust request claim 1 , wherein the controller is configured to meter the flow of the gaseous fuel to satisfy ...

MONITORING SERVO-VALVE FILTER ELEMENTS

A method for determining a state of at least one filter element of at least one servo valve assembly of a gas turbine engine, includes the following steps: Acquiring, by means of a measuring device, a multiplicity of values of a control current of an electric actuator of the servo valve assembly at various points in time and/or in various time periods; and analysing, by means of an analysis device, the multiplicity of values, wherein a change in the control current over time is ascertained, and determining the state of the filter element on the basis of the change in the control current over time. In addition, a system for determining a state of at least one such filter element is made available. 1. A method for determining a state of at least one filter element of at least one servo valve assembly of a gas turbine engine , comprising the following steps:acquiring, by means of a measuring device, a multiplicity of values of a control current of an electric actuator of the servo valve assembly at various points in time and/or in various time periods; andanalysing, by means of an analysis device, the multiplicity of values, wherein a change in the control current over time is ascertained, and determining the state of the filter element on the basis of the change in the control current over time.2. The method according to claim 1 , wherein at the various points in time and/or in the various time periods in each case a profile of the control current with respect to a measure of valve dynamics claim 1 , in particular of an adjustment speed of a servo valve of the servo valve assembly is ascertained.3. The method according to claim 2 , wherein during the analysis of the change in the control current over time claim 2 , the change in the profile of the control current over time is ascertained.4. The method according to claim 1 , wherein the various points in time or time periods correspond to various flights of an aircraft with the gas turbine engine.5. The method ...

Integrated fuel pump and control preservation system

A portable fuel preservation system is disclosed. The portable fuel preservation system may comprise a switch box configured to be coupled to an integrated fuel pump and control of a gas turbine engine. The switch box may comprise a circuit configured to cause a metering valve and a solenoid valve of the integrated fuel pump and control to open. A driver may be configured to inject preservation fluid into the integrated fuel pump and control.

Premixing fuel injectors and methods of use in gas turbine combustor

A fuel injector for a gas turbine combustor includes side wall fuel injection bodies extending between opposite end walls. Each side wall fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in communication with the fuel plenum. One or more fuel injection bodies extending between the end walls are positioned between the side wall fuel injection bodies. Each fuel injection body defines a fuel plenum and includes an outer surface defining fuel injection ports in fluid communication with the fuel plenum. A conduit fitting coupled to the frame is fluidly connected to the respective fuel plenums. The fuel injection ports fluidly communicate with air flow paths defined between the fuel injection bodies and the side wall fuel injection bodies. A combustor for a gas turbine includes a liner and an axial fuel staging system with the present fuel injector.

SYSTEM AND METHOD FOR CONTROLLING A SPEED OF ROTATION OF AN AIRCRAFT TURBINE ENGINE WITH FAULT MANAGEMENT

A system and method for controlling an aircraft turbine engine. The control system includes: a nominal-mode processing chain including a global corrector designed to control a speed of rotation of the turbine engine by delivering a position setpoint for a fuel metering device, and a local corrector designed to control a position of the fuel metering device by delivering a nominal-mode control current, a degraded-mode processing chain including a direct corrector designed to control the speed of rotation of the turbine engine by delivering a degraded-mode control current, and a mode management module designed to deliver, to the fuel metering device, the nominal-mode control current in the absence of failure of a position sensor measuring a position of the fuel metering device, and the degraded-mode control current in the case of failure of the position sensor. 110. A control system for an aircraft turbine engine , the turbine engine () comprising:{'b': '13', 'a combustion chamber (),'}{'b': 12', '11, 'a fuel metering valve including a metering slide (), a position of which determines a volumetric flow rate of fuel injected into the combustion chamber and an actuator () arranged to displace the metering slide depending on a control electric current (I_com),'}{'b': '14', 'a position sensor () arranged to measure a position of the metering slide and deliver a position measurement (M_Pos),'}{'b': '15', 'a speed sensor () arranged to measure a rotational speed of the turbine engine and deliver a rotational speed measurement (M_XNBP), and'}{'b': '16', 'a monitoring unit () arranged to deliver a rotational speed setpoint (C_XNBP), to detect a failure of the position sensor and to deliver a failure signal (Sd) in the case of detection of a failure of the position sensor,'}{'b': '100', 'the control system () comprising{'b': '110', 'a nominal-mode processing chain () including{'b': '21', 'a global corrector () arranged to receive the rotational speed setpoint (C_XNBP) and the ...

GAS TURBINE ENGINE

A gas turbine engine comprising: a combustor configured to initiate combustion; and a turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes; wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring. A method of starting a gas turbine engine is also described. 1. A gas turbine engine comprising:a combustor configured to initiate combustion; anda turbine comprising a stator vane ring defining a plurality of passageways between adjacent vanes;wherein at least one of the passageways is provided with a restrictor which defines a temporary gas washed surface for the stator vane ring and is configured to be ablated upon initiation of combustion to reveal an operational gas washed surface of the stator vane ring.2. The gas turbine engine of claim 1 , wherein the passageway comprises circumferentially extending endwalls between adjacent vanes; and wherein the restrictor is provided on an operational gas washed surface of the endwalls.3. The gas turbine engine of claim 1 , wherein the restrictor is a coating provided on the endwalls claim 1 , and wherein the coating at least partially covers an operational gas washed surface of the endwalls.4. The gas turbine engine of claim 3 , wherein the coating is formed from tin or an alloy of lead and tin.5. The gas turbine engine of claim 1 , wherein the restrictor is provided on the operational gas washed surface of a vane delimiting the passageway.6. The gas turbine engine of claim 5 , wherein the restrictor is a coating provided on a vane delimiting the passageway and wherein the coating at least partially covers the operational gas washed surface of the respective vane.7. The gas turbine engine of claim 6 , wherein the coating completely covers the operational gas washed surface ...

SECONDARY FUEL FLOW DEMAND FUEL PUMPING SYSTEM

A fuel system for a gas turbine engine includes a main fuel pump generating a main fuel flow into a main fuel passage and a secondary pump generating a secondary fuel flow into a secondary flow passage. A first control valve is disposed in a passage between the main fuel passage and the secondary flow passage. The first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow. 1. A fuel system for a gas turbine engine comprising:a main fuel pump generating a main fuel flow into a main fuel passage;a secondary pump generating a secondary fuel flow into a secondary flow passage; anda first control valve disposed in a passage between the main fuel passage and the secondary flow passage, wherein the first control valve selectively directs an excess portion of the main fuel flow to the secondary flow passage to provide at least a portion of the secondary fuel flow.2. The fuel system as recited in claim 1 , including a boost pump drawing fuel from a fuel supply and directing fuel flow to the main fuel pump and the secondary pump.3. The fuel system as recited in claim 2 , including an electric motor driving the secondary pump.4. The fuel system as recited in claim 2 , including a second control valve disposed between the boost pump and the secondary pump claim 2 , the second control valve selectively reducing fuel flow to the secondary pump in response to communication of excess fuel flow from the main passage to the secondary flow passage.5. The fuel system as recited in claim 4 , including a common shaft driving each of the boost pump claim 4 , main pump and secondary pump.6. The fuel system as recited in claim 5 , including a selectively actuated clutch for decoupling the secondary pump from the common shaft.7. The fuel system as recited in claim 5 , wherein the main pump is disposed between the boost pump and the secondary pump.8. The fuel system as recited in claim ...

FUEL CONTROL MODULE

A fuel control module for a gas turbine engine and method of installation. The fuel control module includes a first frame unit, a second frame unit, a fuel path, and a fuel controller components. The first frame unit and the second frame unit include features for installation in multiple installations and/or multiple configurations. 1. A fuel control module for a gas turbine engine , the fuel control module comprising:a primary fuel shut-off valve;a main fuel control valve;a first frame unit, the first frame unit including a first base, a first inner side, and a first outer side, the first inner side and the first outer side joined to opposite sides of the first base and extending perpendicularly from the first base in the same direction, the first base having a first centerline normal to both the first inner side and the first outer side, the first frame unit further including a fuel inlet fluidly aligned with the first centerline and located distal to the first inner side; anda second frame unit, the second frame unit including a second base, a second inner side, and a second outer side, the second inner side and the second outer side joined to opposite sides of the second base and extending perpendicularly from the second base in the same direction, the second inner side configured to align and couple with the first inner side, the second base having a second centerline normal to both the second inner side and the second outer side, the second frame unit further including a fuel outlet configured to deliver fuel to the gas turbine engine and located distal to the second inner side.2. The fuel control module of claim 1 , further comprising:an upstream fuel interface fixed to the first frame unit and fluidly aligned with the first centerline; anda downstream fuel interface fixed to the second frame unit and fluidly aligned with the second centerline, the downstream fuel interface configured to be detachably coupled to the upstream fuel interface.3. The fuel control ...

Split fuel control module

A split fuel control module for a gas turbine engine and method of installation. The split fuel control module includes a first frame unit, a second frame unit, a segmented fuel path, and a distributed fuel controller. The first frame unit and the second frame unit are joined together at a frame unit interface. The segmented fuel path includes an upstream fuel interface fixed to the first frame unit and a downstream fuel interface fixed to the second frame unit and detachably coupled to the upstream fuel interface at the frame unit interface. A first portion of the distributed fuel controller is fixed to the first frame unit, and a second portion of the distributed fuel controller is fixed to the second frame unit.

CONTROLLING COMBUSTION SYSTEM WITH FUEL CHEMICAL INDUCTION TIME

A gas turbine system includes a gas turbine including a combustor for combusting a fuel and a control assembly configured to control at least one of a fuel system and the combusting of the combustor based on providing values corresponding to at least one of fuel characteristics and combustor characteristics to a fuel induction time transfer function. 1. A gas turbine system , comprising:a gas turbine including a combustor for combusting a fuel; anda control assembly configured to control at least one of a fuel system and the combustor based on providing at least one of fuel characteristic values and combustor characteristic values to a fuel induction time transfer function.2. The gas turbine system of claim 1 , wherein control assembly is configured to calculate the fuel induction time transfer function based on pre-defined ranges of fuel characteristic values and combustor characteristic values.3. The gas turbine system of claim 2 , wherein the control assembly is configured to receive the pre-defined ranges of the fuel characteristic values and the combustor characteristic values from at least one of a user input and an external device connected to the control assembly.4. The gas turbine system of claim 1 , wherein the control assembly is configured to measure fuel characteristics and combustor characteristics and to control at least one of the fuel system and the combustor based on a fuel induction time value resulting from providing at least one of measured fuel characteristic values and measured combustor characteristic values to the fuel induction time transfer function.5. The gas turbine system of claim 1 , wherein the control assembly is configured to control at least one of the fuel system and the combustor based on providing a fuel induction time value generated by the fuel induction time transfer function to a gas turbine control model claim 1 , and to generate at least one of fuel system control signals and combustor control signals based on outputs ...

Method of operating a multi-stage flamesheet combustor

The present invention discloses a novel way of controlling a gas turbine engine using detected temperatures and detected turbine rotor speed. An operating system provides a series of operating modes for a gas turbine combustor through which fuel is staged to gradually increase engine power, yet harmful emissions, such as carbon monoxide, are kept within acceptable levels.

GAS TURBINE SYSTEM AND METHOD

A fuel supply system is provided having a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system. The first fuel gas compressor and the second fuel gas compressor are configured to supply a pressurized fuel flow to a combustor of the gas turbine system, and the first fuel gas compressor and the second fuel gas compressor are coupled to one another in series. 1. A system , comprising: a first fuel gas compressor coupled to a compressor shaft and configured to pressurize a fuel for a gas turbine system;', 'a first clutch configured to selectively engage the compressor shaft with a motor shaft of a motor; and', 'a second clutch configured to selectively engage the compressor shaft with a turbine shaft of the gas turbine system., 'a fuel supply system, comprising2. The system of claim 1 , wherein the first fuel gas compressor comprises a plurality of inlet guide vanes.3. The system of claim 2 , comprising a gearbox coupled to the compressor shaft.4. The system of claim 1 , comprising the gas turbine system claim 1 , wherein the gas turbine system comprises:a compressor configured to pressurize an oxidant;a combustor configured to combust the oxidant supplied by the compressor and the fuel supplied by the first fuel gas compressor into combustion products; anda turbine coupled to the turbine shaft and configured to extract work from the combustion products to rotate the turbine shaft.5. The system of claim 4 , comprising the motor coupled to the motor shaft.6. The system of claim 4 , wherein the fuel supply system comprises a second fuel gas compressor coupled to the turbine shaft of the gas turbine system and configured to pressurize the fuel.7. The system of claim 6 , wherein the fuel supply system comprises a fuel flow path claim 6 , the first and second fuel gas compressors are disposed along the fuel flow path claim 6 , and the second fuel gas compressor is disposed ...

GAS TURBINE ACTIVE COMBUSTION INSTABILITY CONTROL SYSTEM

A turbine active combustion instability control system comprising a primary passage to a combustor of a turbine; a combustor pressure sensor configured to measure dynamic pressure within the combustor; a pilot valve metering fuel flow through a pilot passage to the combustor and comprising a valve seat defining a throat in the pilot passage and a valve plug movable to control fuel flow through the throat, the pilot valve having an inlet passage with a contoured surface to accelerate gas flow through the throat to at least Mach 1; a dynamic linear motor actuator connected to the valve plug and configured to actuate the valve plug at a high frequency; and a controller configured to provide a control signal to the actuator as a function of input from the combustor pressure sensor. 1. A gas turbine active combustion instability control system comprising:a primary fuel flow passage to a combustor of a combustion turbine;a combustor pressure sensor configured to measure a dynamic pressure within said combustor;a pilot fuel flow passage to said combustor; a pilot metering valve body having a valve seat defining a throat in said pilot flow passage between said upstream side and said downstream side;', 'a pilot metering valve plug movable relative to said pilot metering valve body from an open position to a closed seated position to control fuel flow through said throat from said upstream side to said downstream side;', 'said pilot metering valve body having an inlet passage on said upstream side of said throat, said inlet passage having a contoured surface generally angled to narrow toward said throat and to accelerate gas flow through said throat to at least Mach 1;', 'said pilot metering valve body having an outlet passage on said downstream side of said throat;, 'a pilot control valve configured to meter fuel flow through said pilot flow passage to said combustor from an upstream side to a downstream side, said pilot control valve comprisinga dynamic linear motor ...

Dual schedule flow divider valve, system, and method for use therein

A passive flow splitting system for use in a turbine engine control system to provide split fuel flow to two fuel manifolds to supply primary and secondary fuel injectors for the particular combustion zones thereof utilizing intentionally different split ratios dependent on ascending or descending combustion fuel flow is provided. The system includes a passive fuel divider valve (FDV) that includes a primary piston and a secondary piston. The primary piston is moveable independently from the secondary piston during a portion of its stroke, and is hydro-locked to the secondary piston during another portion of its stroke. An ecology valve is also provided to purge the fuel from the primary and/or secondary manifolds during different modes of operation. A transfer valve is included to control the position of ecology piston of the ecology valve.

Gas Turbine and Method for Adjusting Flow Rate of Fuel Supplied Thereto

A gas turbine including a fuel gas supply system to supply fuel gas via a fuel piping to a gas turbine combustor, a pressure control valve installed halfway along the fuel piping, a flow control valve installed in the fuel piping at downstream of the pressure control valve, and a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P1 at upstream of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P1. 1. A gas turbine comprising:a fuel gas supply system configured to supply fuel gas from a fuel supply equipment via a fuel piping to a gas turbine combustor;a pressure control valve installed halfway along the fuel piping to control pressure of the fuel gas;a flow control valve installed in the fuel piping at a downstream side of the pressure control valve to control a flow rate of the fuel gas; and{'b': ['1', '1'], '#text': 'a control device configured that in a case where a flow rate change occurs in the fuel gas flowing through the fuel gas supply system, along with a tendency of change in an opening degree of the pressure control valve or a pressure P at an upstream side of the pressure control valve, a command value of the flow rate of the fuel gas that is determined based on a demand value of a gas turbine load is adjusted so that the change is suppressed in the opening degree of the pressure control valve or the pressure P at the upstream side of the pressure control valve.'}2. The gas turbine according to claim 1 ,wherein a fuel gas extraction line to other equipment and a fuel gas return line from the other equipment are connected to upstream of the fuel gas supply system, and ...

ACTIVE CONTROL FUEL NOZZLE SYSTEM

It is desirable for a gas turbine system to operate in a wide range operating conditions. However, under certain conditions there exist dynamic boundaries that limit a combustor from reaching its designated condition. Perturbation devices formed of electromagnetic plates can be incorporated into fuel nozzles of the combustor to influence the dynamics so that the range of operating conditions can be widened. The perturbation devices vibrate according to the perturbation signals provided from a dynamics controller. The vibration characteristics of the perturbation devices can be controlled by controlling the attributes of the perturbation signals. The vibrations influence the dynamics of fluid—fuel, oxidant, or both—flowing past the perturbation devices within the fuel nozzles. 1. A perturbation device for use in a fuel nozzle of a combustor of a gas turbine system , the perturbation device comprising:a plurality of flexible plates including first and second flexible plates, both the first and second flexible plates being electromagnetic plates,wherein the first and second flexible plates are respectively structured to receive first and second perturbation signals and generate corresponding first and second magnetic fluxes,wherein the first and second flexible plates are physically disposed relative to each other such that one or both of the first and second flexible plates vibrate due to an interaction between the first and second magnetic fluxes, andwherein the first flexible plate is structured to receive an AC signal as the first perturbation signal and generate a corresponding AC magnetic flux as the first magnetic flux.2. The perturbation device of claim 1 , wherein one of the first and second flexible plates is structured to be stationary and the other of the first and second flexible plates is structured to vibrate due to the interaction between the first and second magnetic fluxes.3. The perturbation device of claim 1 , wherein the second flexible plate is ...

High Pressure Turbine Speed Calculation from Fuel System Hydraulic Pressures

The speed of a high-pressure turbine of a gas turbine engine may be determined using known centrifugal pump affinity relationships for a fuel pressure apparatus, fuel pressure apparatus input and output pressures, and gear ratios for a mechanical linkage between the high-pressure turbine and the fuel pressure apparatus. The technique avoids wear-related variations in gas pressure based measurements and also applies to fuel pressure apparatus using both single pump and multiple pump configurations. 1. A method of determining a speed of a high pressure turbine in a gas turbine engine , the method comprising:providing a nominal output fuel pressure of a fuel pressure apparatus when the high pressure turbine is operating at a nominal speed;determining a first fuel pressure at an input of the fuel pressure apparatus that supplies fuel to a combustion chamber of the gas turbine engine;determining a second fuel pressure at an output of the fuel pressure apparatus; andcalculating the speed of the high pressure turbine as a quadratic relationship of the first fuel pressure of the fuel pressure apparatus and the second fuel pressure of the fuel pressure apparatus.2. The method of claim 1 , wherein the fuel pressure apparatus is a single stage centrifugal pump.3. The method of claim 2 , further comprising calculating a shaft speed of the single stage centrifugal pump claim 2 , wherein calculating the speed of the high pressure turbine is a function of the shaft speed and a gear ratio of a gear box coupling the high pressure turbine and the single stage centrifugal pump.4. The method of claim 1 , wherein the fuel pressure apparatus is a multiple stage pump including a plurality of centrifugal pumps.5. The method of claim 4 , further comprising driving each stage of the multiple stage pump at a common speed proportional to a gear ratio of a gear box coupling the high pressure turbine and the multiple stage pump.6. A system for determining a speed of a high pressure turbine in a ...

FUEL ROUTING SYSTEM OF A GAS TURBINE ENGINE AND METHOD OF ROUTING FUEL

A fuel routing system of a gas turbine engine includes a primary fuel circuit in communication with a fuel source and a fuel distribution manifold. Also included is a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to a plurality of combustor chambers. Further included is a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine. Yet further included is a plurality of check valves disposed between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow between the secondary fuel circuit and the primary fuel circuit. 1. A fuel routing system of a gas turbine engine comprising:a primary fuel circuit feeding a fuel distribution manifold which directs fuel to a combustor chamber;a secondary fuel circuit extending from the primary fuel circuit to a plurality of fuel nozzles configured to direct fuel to the combustor chamber;a main fuel flow control valve disposed in the primary fuel circuit for restricting a fuel flow to the fuel distribution manifold upon removal of an electrical load operably coupled to the gas turbine engine; anda plurality of check valves located between the secondary fuel circuit and the primary fuel circuit for restricting the fuel flow from the secondary fuel circuit to the primary fuel circuit.2. The fuel routing system of claim 1 , wherein the secondary fuel circuit comprises a plurality of fuel lines each in communication with one of the plurality of fuel nozzles.3. The fuel routing system of claim 1 , wherein the plurality of fuel nozzles comprises a portion of a total number of fuel nozzles of the gas turbine engine.4. The fuel routing system of claim 3 , wherein the portion of the total number of fuel nozzles is a subset of the total number of fuel nozzles.5. The fuel routing system of claim 1 ...

BLEED VALVE OVERRIDE SCHEDULE ON OFF-LOAD TRANSIENTS

In one aspect, the present disclosure is directed to a method for controlling a position of a bleed valve of a gas turbine engine. The onset of an off-load transient may be determined. Values representative of the turbine rotor inlet temperature and the exhaust outlet temperature may be determined. Also, the amount of time elapsed since the onset of the off-load transient may be determined. Three provisional bleed valve command positions may be determined based on value representative of the turbine rotor inlet temperature, the value representative of the exhaust outlet temperature, and the amount of time elapsed, respectively. The provisional bleed valve command position associated with the lowest relative value may be selected. Then, the bleed valve position may be adjusted to match the selected bleed valve command position. 1. A method for controlling a position of a bleed valve of a gas turbine engine , comprising:a) determining an onset of an off-load transient;b) determining a value representative of a turbine rotor inlet temperature, a value representative of an exhaust outlet temperature, and an amount of time elapsed since onset of the off-load transient;c) determining a first provisional bleed valve command position value based on the value representative of the turbine rotor inlet temperature;d) determining a second provisional bleed valve command position based on the value representative of the exhaust outlet temperature;e) determining a third provisional bleed valve command position based on the time elapsed since onset of the off-load transient;f) determining which of the first, second, and third provisional bleed valve command positions is associated with a lowest relative value and selecting the provisional bleed valve command position associated with the lowest relative value; andg) adjusting the position of the bleed valve to match the selected bleed valve command position.2. The method of claim 1 , further including claim 1 , after an initial ...

SYSTEMS AND METHODS FOR STARTING A GAS TURBINE ENGINE

Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine. 1. A method for starting an aircraft gas turbine engine , the method comprising:in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up;in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; andin a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.2. The method of claim 1 , wherein the second phase is initiated when light-up is detected claim 1 , and the third phase is initiated when the conditions for light-around are met.3. The method of claim 1 , further comprising claim 1 , in a fourth phase of the startup claim 1 , modifying a fourth set of engine control parameters to transition to a closed loop fuel control.4. The method of claim 3 , wherein the fourth phase is initiated when complete ignition is detected.5. The method of claim 1 , wherein modifying the first set of engine control parameters comprises applying an adaptive fuel flow logic as a function of a first set of operating parameters.6. The method of claim 5 , wherein modifying the first set of engine control parameters further comprises transitioning variable geometry mechanisms (VGMs) of the engine from a windmilling position to an ignition position and setting an ignition frequency based on a second set of operating parameters.7. The method of claim 1 , wherein ...

FUEL METERING CIRCUIT AND METHOD WITH COMPENSATION FOR FUEL-DENSITY VARIABILITY

A fuel metering circuit for a turbomachine includes: a meter; a pump; a control valve configured to return an excess flow of fuel delivered to the meter towards the pump on the basis of a fuel pressure differential at the terminals of the meter; a diaphragm; and a volumetric flow meter. The diaphragm and the volumetric flow meter are mounted parallel to the meter, downstream of the control valve, in order to determine a density of the fuel flowing in the metering circuit. 1. A fuel metering circuit for a turbomachine comprising:a metering device;a pump configured to circulate a fuel flow rate toward the metering device;a regulating valve configured to return an excess fuel flow rate delivered to the metering device toward the pump according to a difference in fuel pressure at terminals of the metering device;a diaphragm; anda volume flow meter configured to determine a volume flow rate of fuel passing through the diaphragm,wherein the diaphragm and the volume flow meter are mounted in parallel with the metering device in a bypass duct, downstream of the regulating valve, in order to determine a density of the fuel circulating in the metering circuit.2. The metering circuit according to claim 1 , wherein the volume flow meter is mounted upstream or downstream of the diaphragm.3. The metering circuit according to claim 1 , further comprising an electronic card configured to receive information from the volume flow meter on the volume flow rate of the fuel and adjust a metering device monitoring setpoint by taking into account the fuel density thus determined.4. The metering circuit according to claim 1 , wherein the pump comprises a volumetric pump.5. A turbomachine comprising a fuel metering circuit according to .6. A fuel metering method implemented in a fuel metering circuit according to claim 1 , the method comprising:determining the difference in fuel pressure at the terminals of the metering device;measuring the volume flow rate of the fuel using the volume flow ...