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.

УСТРОЙСТВО ДЛЯ ЗАПУСКА ПАРОВОЙ ТУРБИНЫ ПОД НОМИНАЛЬНЫМ ДАВЛЕНИЕМ

Изобретение относится к энергетике. Система генерации электроэнергии с комбинированным циклом, содержащая внешний байпасный контур управления запуском с регулирующим клапаном для паровой турбины, облегчающий работу энергетической установки при максимальном давлении. Также представлены устройство для регулирования потока пара в паровую турбину при быстром запуске установки с комбинированным циклом и способ запуска системы генерации электроэнергии с комбинированным циклом. Изобретение позволяет управлять дросселированием в тяжелых условиях эксплуатации в ходе запуска паровой турбины под высоким давлением. 3 н. и 7 з.п. ф-лы, 6 ил.

СПОСОБ И СИСТЕМА ДЛЯ НАДЕЖНОГО ЗАПУСКА ТУРБИННОГО ДВИГАТЕЛЯ

Система запуска турбинного двигателя содержит аккумуляторную батарею, стартер постоянного тока, электронный вычислитель регулирования, редуктор трансмиссии, пусковые вспомогательные устройства, газогенератор, который в свою очередь содержит компрессор, камеру сгорания и турбину высокого давления вместе со свободной турбиной. Первая и вторая цепи соединяются параллельно и размещаются между упомянутой аккумуляторной батареей и стартером постоянного тока. Первая цепь содержит преобразователь постоянного тока в постоянный ток, соединенный последовательно с первым переключателем, а вторая цепь содержит второй переключатель. Система дополнительно содержит, по меньшей мере, датчик для измерения скорости вращения компрессора, датчик для измерения температуры на входе в свободную турбину и схему управления для управления первым и вторым переключателями в зависимости от информации, предоставляемой посредством датчика для измерения скорости вращения компрессора и посредством датчика для измерения ...

СПОСОБ КОНТРОЛЯ СТЕПЕНИ ЗАБИВАНИЯ ПУСКОВЫХ ФОРСУНОК ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Изобретение относится к энергетике. Способ контроля степени забивания пусковых форсунок газотурбинного двигателя, содержащего камеру сгорания, в которую открыта по меньшей мере одна питаемая топливом пусковая форсунка, при этом указанные пусковые форсунки выполнены с возможностью инициации горения в указанной камере посредством воспламенения топлива, и турбину, приводимую во вращение газообразными продуктами горения топлива в камере. При этом способ содержит этапы, на которых во время фазы запуска газотурбинного двигателя измеряют (1100) температуру отработанных газов на выходе из турбины и на основании изменения по времени измеряемой температуры определяют (1200) степень забивания пусковых форсунок. Также представлены система контроля степени забивания, выполненная с возможностью осуществления способа контроля согласно изобретению, а также газотурбинный двигатель и летательный аппарат, содержащие такую систему. Изобретение позволяет обеспечить возможность обнаружения забивания пусковых ...

КОНСТРУКЦИЯ СИЛОВОЙ УСТАНОВКИ ВЕРТОЛЕТА, СОДЕРЖАЩЕЙ ГИБРИДНЫЙ ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ И СИСТЕМУ ПОВТОРНОГО ПРИВЕДЕНИЯ В ДЕЙСТВИЕ ЭТОГО ГИБРИДНОГО ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Изобретение относится к конструкции силовой установки многодвигательного вертолета, содержащей газотурбинные двигатели, соединенные с редуктором силовой трансмиссии, отличающейся тем, что она содержит, по меньшей мере, один гибридный газотурбинный двигатель (20), который способен функционировать, по меньшей мере, в одном режиме ожидания во время установившегося полета с крейсерской скоростью вертолета; по меньшей мере, две проверочных цепи (30; 40) каждого гибридного газотурбинного двигателя (20); причем каждая цепь (30; 40) содержит электрическую машину (31; 41), соединенную с гибридным газотурбинным двигателем (20) и приспособленную для приведения его газогенератора во вращение, и, по меньшей мере, один источник (33; 43) электропитания этой электрической машины (31; 41); причем каждая цепь (30; 40) повторного приведения в действие рассчитана таким образом, чтобы имелась возможность перевода упомянутого газотурбинного двигателя (20), по меньшей мере, в один рабочий режим из множества предварительно ...

СПОСОБ УПРАВЛЕНИЯ ГАЗОПАРОТУРБИННОЙ УСТАНОВКОЙ С ЧАСТОТНЫМ ПРЕОБРАЗОВАТЕЛЕМ

Изобретение относится к энергетике. В способе управления газопаротурбинной установкой, содержащей связанный с пусковым устройством газовой турбины частотный преобразователь и связанный с паровой турбиной генератор, электрическая мощность от генератора при оборотах турбины меньших, чем частота турбины, или в процессе прогрева подается в электрическую сеть общего пользования через частотный преобразователь. Кроме того, предложена газопаротурбинная установка, подходящая для осуществления способа. Изобретение позволяет при низких конструкционных затратах достигнуть высокой эксплуатационной гибкости. 1 з.п. ф-лы, 1 ил.

ЛИНИЯ ГЕНЕРАТОРА - ПАРОВОЙ ТУРБИНЫ - ТУРБОКОМПРЕССОРА И СПОСОБ ДЛЯ ЕЕ ЭКСПЛУАТАЦИИ

Изобретение относится к энергетике. Линия генератора - паровой турбины - турбокомпрессора, содержит изменяемый по частоте генератор, паровую турбину и турбокомпрессор, приводимый генератором и/или паровой турбиной, которые взаимосвязаны валопроводом, причем генератор электрически связан с электрической сетью для сетевого питания, а паровая турбина имеет возможность подключения к устройству подачи свежего пара для подачи свежего пара к паровой турбине, так что линия генератора - паровой турбины - турбокомпрессора посредством изменения сетевого питания и/или посредством подачи свежего пара имеет возможность регулирования по числу оборотов. Изобретение позволяет повысить КПД и обеспечить хорошую регулируемость при незначительных инвестиционных затратах. 2 н. и 5 з.п. ф-лы, 3 ил.

СПОСОБ ЗАПУСКА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

Использование: в энергетике. Сущность изобретения: во время запуска подают сжатый воздух в проточную часть турбины, расположенную за первым участком расширения рабочего тела, причем сжатый воздух отбирают от ступеней компрессора, устойчиво работающих при запуске. 2 ил.

СПОСОБ РАБОТЫ ЭЛЕКТРОСТАНЦИИ

... 1. Способ работы тепловой электростанции, содержащей парогенератор (16), паровую турбину (17, 18, 19) и пароводяной цикл (20), по меньшей мере, состоящий из конденсатора (21) с водяным охлаждением, деаэратора (29) и питательного водяного насоса (26), при этом насос (22) для охлаждающей воды предоставлен для перекачивания охлаждающей воды через упомянутый конденсатор (21) с водяным охлаждением, и вакуумирующее средство (25) соединено с упомянутым конденсатором (21) с водяным охлаждением для вакуумирования, по меньшей мере, упомянутого конденсатора (21) с водяным охлаждением, при этом упомянутый способ работы относится к остановке и пуску упомянутой электростанции (10) после упомянутой остановки и содержит этапы:a) остановки паровой турбины (17, 18, 19);b) восстановления хорошего вакуума внутри конденсатора (21) с применением упомянутого вакуумирующего средства (25);c) выключения упомянутого насоса (22) для охлаждающей воды упомянутого конденсатора (21) с водяным охлаждением и упомянутого ...

СИСТЕМА ЗАЖИГАНИЯ КАМЕРЫ СГОРАНИЯ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ

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 ...

ВСТАВКА ДЛЯ ТУРБОКОМПРЕССОРА

Flugzeugtriebwerk und Verfahren zur Kupplung oder Entkupplung einer Kupplungsvorrichtung in einem Gasturbinentriebwerk

Die Erfindung betrifft ein Gasturbinentriebwerk (10) für ein Luftfahrzeug, umfassend: ein Kerntriebwerk (11), das eine Turbine (19), einen Verdichter (14) und eine die Turbine mit dem Verdichter verbindende Kernwelle (26) umfasst;einen Fan (23), der stromaufwärts des Kerntriebwerks (11) positioniert ist, wobei der Fan (23) mehrere Fanschaufeln umfasst; undein Planetengetriebe (30), das von der Kernwelle (26) antreibbar ist, wobei der Fan (23) mittels des Planetengetriebes (30) mit einer niedrigeren Drehzahl als die Kernwelle (26) antreibbar ist,dadurch gekennzeichnet, dassein feststehendes Teil (38, 55) des Planetengetriebes (30) über eine Kupplungsvorrichtung (50) mit einem statischen Bauteil (51) des Gasturbinentriebwerks (10) schaltbar verbunden ist und eine Ölkammer (52) zur Versorgung einer Schaltung der Kupplungsvorrichtung (50) mit dem Ölsystem des Gasturbinentriebwerks (10) verbunden ist, wobei der Öldruck (p) in der Ölkammer (52) so einstellbar ist, dass nominelle Reaktionsdrehmomente ...

Einrichtung zur Sicherung von Dampfturbinen mit Speicherraeumen, insbesondere mit Zwischenueberhitzung

Kombianlage, Verfahren zur Steuerung derselben und Vorrichtung für die Steuerung derselben

Steuervorrichtung (100) für eine Kombianlage, wobei die Kombianlage eine Gasturbine (10), die durch ein Verbrennungsgas angetrieben wird, einen Abgaswärmerückgewinnungskessel (20), der Dampf unter Verwendung von Wärme des Verbrennungsgases, das von der Gasturbine (10) abgegeben wird, erzeugt, eine erste und eine zweite Dampfturbine (31,32), die durch den Dampf angetrieben werden, und einen Kondensator (36) umfasst, der den Dampf, der von der zweiten Dampfturbine (32) abgegeben wird, zurück zu Wasser kondensiert, wobei der Abgaswärmerückgewinnungskessel (20) ein erstes Dampf erzeugendes Teil (21), das unter Verwendung der Wärme des Verbrennungsgases den ersten Dampf erzeugt, der die erste Dampfturbine (31) versorgt, und einen Zwischenüberhitzungsabschnitt (26) umfasst, der den Dampf, der von der ersten Dampfturbine (31) abgegeben wird, erhitzt, wobei das erste Dampf erzeugende Teil (21) des Abgaswärmerückgewinnungskessels (20) und die erste Dampfturbine (31) durch eine erste Dampfleitung ...

Verfahren zum Betreiben einer Turbine

Method for starting power station installation in deactivated electricity network, involves forming connection between generator of pressure store-relaxation turbine and start device of gas turbine group

A method for starting a power station installation in a deactivated electrical network, in which the power station comprises a pressurized air store (201) and a pressure store-relaxation turbine (203) and a gas turbo group (1). The procedure comprises opening a storage fluid mass flow adjustment element (7) and taking a storage fluid mass flow out of the pressurized air store. The storage fluid mass flow is then relaxed in the pressure store-relaxation turbine by generating a shaft output and then driving the generator (204) with the generated shaft output and generating a first electrical output. A connection is formed between the generator (204) and pressure store-relaxation turbine and a start device (22) of the gas turbine group. The gas turbo group is then started with the electrical power generated by the generator of the pressure store-relaxation turbine. An electrical connection is then made between the power station installation and the electricity network. An independent claim ...

AUTOMATISCHES ANLAUF-SYSTEM FUER EINE GESCHLOSSENE CLAUSIUS-RANKINE-PROZESS-KRAFTANLAGE

Anlasseinrichtung fuer Gleichdruckdampf-. Luft- oder Gasturbinen mit Geschwindigkeitsstufen

Aircraft engine constant frequency starter/generator

A constant frequency starter/generator 55 for an aircraft turbine engine includes: a first inverter/converter 56 electrically connected to a second inverter/converter 60 via a DC link 58; and an electric machine assembly 10 having a synchronous main machine and an exciter, wherein the starter/generator 55 is operable in a starting mode and a generating mode. In a starting mode, the first inverter/converter 56 receives a constant frequency AC input 62 from an external power source. The first inverter/converter 56 converts the AC input 62 to a DC output 68 which is supplied to a DC input 74 of the second inverter/converter 60. The second inverter/converter 60 converts the DC input 74 to an AC output 72 to start the main machine. In a generating mode, the main machine supplies generated AC power via an AC output 86 to an AC input of the second inverter/converter 70. The second inverter/converter 60 converts the AC input 70 to a DC output 76 which is supplied to a DC input 66 of the first inverter ...

Aircraft engine constant frequency starter/generator

Control System for turbines.

... 1,167,003. Valves. WESTINGHOUSE ELECTRIC CORP. 6 Sept., 1967 [13 Oct., 1966], No. 40668/67. Heading F2V. [Also in Divisions F1 and G3] In a valve 581 forming part of a steam turbine governing system (see Divisions G2-G3), a fluid pressure signal at 67 is admitted via passage 70 to chamber 61 to depress piston 59 to disconnect chambers 62, 63 and connect the latter to chamber 64. In the depressed position of piston 59, passage 70 is cut off from signal line 67 and connected to chamber 62 to admit fluid to chamber 61 to retain the piston in the depressed position. A magnet 76 carried by the piston actuates a switch 78 to cut off the signal in line 67.

STEAM TURBINE CONTROL

Generating electrical power at high thrust conditions

A gas turbine engine for an aircraft comprising a high pressure (HP) spool, HP compressor 105, a first electric machine 117 having a first maximum output power and driven by HP turbine 107, low-pressure (LP) spool, a second electric machine 119 having a second maximum output power and driven by LP turbine 108, an engine controller 123 configured to identify a condition to the effect that the engine is in a maximum take-off mode of operation or a maximum climb mode of operation, and, in response to an electrical power demand being between zero and the second maximum output power, only extract electrical power from the second electric machine to meet the electrical power demand. Maximum take-off or maximum climb modes may be identified by comparing one or more of the altitude, the Mach number and the power lever angle. Both electric machines may be motor-generators.

Automatic starting device for putting steam turbines into operation

... 619,726. Steam turbines. ANSALDO SOC. ANON. Dec. 20, 1946, No. 37574. Convention date, April 28, 1941. [Class 110 (iii)] An arrangement for starting a steam turbine, in which the regulating valves are normally operated by pressure oil under a pressure controlled by the speed-governor, comprises a series of valves 30-33 operated by cams 24-27 on a manually-operated shaft 20. The speedgovernor 3, receives oil from a regulating pump 2 which is fed by a main pump 1. Pressure oil from the governor passes through a non-return valve 4 to the operating cylinders of the turbine valves 5, 6, 7. When the turbine is at rest, the control oil pipe between the governor 3 and valve 4 is connected to waste through the valve 31. In starting the shaft 20 is turned in steps. At the first, valves 30 and 32 are opened. Valve 30 admits steam to an auxiliary oil pump 11, which thereupon delivers oil through a restricted orifice 13 to the bearings, and the valve 32 connects the delivery of that pump to the control ...

TURBINE

... 1482792 Turbines LICENTIA PATENTVERWALTUNGS GmbH and AEG-KANIS TURBINENFABRIK GmbH 15 Oct 1974 [18 Oct 1973] 44689/74 Heading F1T An axial-flow gas turbine includes inlet nozzles 1, rotor blades 4, an outlet channels 5 aligned with the outlet direction of the rotor blades so that low flow losses at low speeds allow a short starting time, whereas high flow losses at the rated speed ensure that the torque/speed characteristic curve is steep at this point for stability.

Starting device for gas turbine engine

Turbine apparatus

... 904,967. Fluid-pressure servomotor-control systems. WESTINGHOUSE ELECTRIC CORPORATION. June 27, 1961 [Aug. 11, 1960], No. 23223/61. Class 135. [Also in Group XXVI] The invention relates to a system for con- trolling the acceleration of an elastic-fluid turbine power plant having a plurality of turbine units driving separate power output shafts. The plant shown comprises a first turbine group 11 driving an electric generator 15, and a second turbine group 17 driving an electric generator 20, the first turbine group comprising a highpressure steam turbine 12 and a low-pressure steam turbine 13 of the double-flow type mounted in tandem on a common shaft 14. The second turbine group comprises an intermediate pressure steam turbine 18 of the double-flow type and a low-pressure steam turbine 19 also of the double-flow type, mounted in tandem on a common shaft 22. High pressure steam from the steam boiler 35 flows through line 34 to the H.P. turbine 12, the steam discharging therefrom passing ...

Aircraft fuel management

A method 2000 of identifying a fuel contained in a fuel tank of an aircraft and arranged to power a gas turbine engine of the aircraft is performed by processing circuitry of the aircraft. The method comprises obtaining 2002 a fuel characteristic of fuel already present in the fuel tank prior to refuelling and then determining 2004 a fuel characteristic of fuel added to the fuel tank on refuelling, then and calculating 2006 a fuel characteristic of the resultant fuel in the fuel tank after refuelling. The method 2000, when controlling the propulsion system of the aircraft further comprises controlling 2008 the propulsion system based on the calculated fuel characteristic of the resultant fuel in the fuel tank after refuelling. The propulsion system comprises a gas turbine engine (10, fig. 4), fuel tanks (50, 53, fig. 4) and a fuel composition tracker (202, fig. 4). The fuel composition tracker stores current fuel characteristic data, obtains a characteristic of the fuel added to the tank ...

Solar energy and external source steam complementary power generation apparatus

SOLAR ENERGY AND EXTERNAL SOURCE STEAM COMPLEMENTARY POWER GENERATION APPARATUS

Solar energy and external source steam complementary power generation apparatus

Solar energy and external source steam complementary power generation apparatus

PROCEDURE AND DEVICE FOR THE REPRESENTATION OF THE OPERATING CONDITION OF A TURBINE DURING A STARTING PROCESS

Device to ready for use stops and kinds of snapping of steam turbines

Procedure for the production of new 6-Alkoxy-pyridaziniumverbindungen

SELF-SHIFTING CLUTCH

Solar energy and external source steam complementary power generation apparatus

A solar energy and external source steam complementary power generation apparatus comprising a solar steam generation device, an external source steam regulator (15), a turboset (2) and a generator (1). A steam output end of the solar steam generation device is connected to a high-pressure steam inlet (3) of the turboset (2) through a first regulating valve (15); a steam output end of the external source steam regulator (15) is connected to the high-pressure steam inlet (3) of the turboset (2) through a second regulating valve (20) and a second switching valve (19). A low-pressure steam outlet (4) of the turboset (2) is connected to a circulating water input end of the solar steam generation device through a condenser (5), a deaerator (6), a water feed pump (7) and a first switching valve (16) in turn. An output end of the water feed pump (7) is connected to an external source steam water return bypass (11) through a fourth switching valve (23).

TURBINE ACCELERATION GOVERNING SYSTEM

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.

ELECTRIC POWER PLANT AND TURBINE ACCELERATION CONTROL SYSTEM FOR USE THEREIN

ENGINE TURNING MOTOR VIA PNEUMATIC OR HYDRAULIC MOTOR

Pressurized fluid is stored while a jet engine is running. After engine shutdown, the fluid is used to drive a pneumatic or hydraulic turning motor that rotates the engine's High Pressure (HP) rotor. The rotation encourages even heat distribution across the HP rotor and thus prevents bowing of the HP rotor.

PLANETARY GEAR SYSTEM AND AIR TURBINE STARTER

An apparatus for an air turbine starter for an engine. The air turbine starter includes a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas and having a turbine output shaft. The air turbine starter further includes a planetary gear system drivingly coupled with the turbine output shaft and including a sun gear, a ring gear mounted to the housing, and a set of planetary gears operably coupling the sun gear and the ring gear with the sun gear is coupled to the turbine output shaft.

COMPRESSED AIR ENERGY STORAGE POWER GENERATION APPARATUS AND COMPRESSED AIR ENERGY STORAGE POWER GENERATION METHOD

Provided is a compressed air energy storage power generation device that preferentially restarts whichever is warmed up from among compressors and electric motors that are stopped, or from among expanders and power generators that are stopped. A compressed air energy storage power generation device 1 comprises: electric motors 10-13; compressors 20-23 that compress air; a pressure accumulation tank 40 that accumulates compressed air; expanders 60-63 that are driven by the compressed air supplied from the pressure accumulation tank; power generators 70-73; and a control device 80 that controls the driving of the electric motors 10-13. The control device 80 includes: a power supply command receiving unit 82 that receives a power supply command; a priority order setting unit 81 that sets a priority order in each electric motor, the priority order being higher as the time from when the electric motor stopped is shorter; an electric motor number determination unit 83 that determines the number ...

APPARATUS AND METHOD FOR CONTROLLING ENGINE WINDMILLING

An apparatus and method are provided for controlling the ground windmilling of at least one of the spools in a gas turbine engine. Electrical power is supplied to a braking apparatus in one aspect. In another aspect, an oil system is powered during ground windmilling.

TURBOFAN ENGINE WITH GENERATOR

A turbofan engine includes a turbine engine having a rotatable fan and a generator. The generator further includes a main machine, an exciter, and a generator control unit for controlling the excitation of the main machine. A rotor assembly is located within one of the blades, and a stator assembly that is along a rotational path of the rotor assembly whereby the operation of the turbine engine rotates the fan, which rotates the rotor assembly along its rotational path past the stator assembly to generate electricity.

METHODS AND SYSTEMS FOR OPERATING A GAS TURBINE ENGINE

A method of operating a gas turbine engine may include operating a starter motor to rotate a spool of the gas turbine engine; determining a torque of the starter motor during rotation of the spool; and controlling the rotation of the spool based on the torque.

SYSTEM AND METHOD FOR THE EMERGENCY STARTING OF AN AIRCRAFT TURBOMACHINE

Système (20) de démarrage d'urgence de turbomachines d'aéronef, comprenant au moins un générateur de gaz (22) à propergol solide, un dispositif d'allumage (24) commandé électriquement, un calculateur (28) relié au dispositif d'allumage, et au moins deux démarreurs (18) indépendants destinés chacun au démarrage d'une turbomachine, chaque démarreur comportant une turbine (38) d'entraînement d'un arbre (34) destiné à être couplé à un arbre (54) de la turbomachine correspondante, la sortie des gaz du générateur étant reliée à l'entrée (44) de la turbine de chaque démarreur par une même vanne de distribution (26) reliée au calculateur (28).

METHOD FOR STARTING A TURBOMACHINE

L'invention concerne un procédé de démarrage pour une turbomachine. L'invention se caractérise par le fait que le procédé comporte en outre une étape de relance réalisée si l'injecteur principal n'est pas allumé alors que l'arbre a atteint une première valeur de vitesse prédéterminée, ladite étape de relance comprenant : - une étape d'arrêt (S210) au cours de laquelle le démarreur et le dispositif d'allumage sont arrêtés; - une seconde étape d'allumage (S230) au cours de laquelle du carburant est injecté dans la chambre de combustion, le dispositif d'allumage étant quant à lui actionné, cette seconde étape d'allumage étant réalisée lorsque la vitesse de rotation de l'arbre atteint une seconde valeur de vitesse prédéterminée; et - une seconde étape de démarrage (S250) au cours de laquelle le démarreur est à nouveau actionné afin d'entraîner l'arbre en rotation.

Verfahren für das Anfahren mit einem mit Dampfturbinen, Mehrphasengeneratoren und Asynchronmotoren ausgerüsteten Fahrzeug.

Dispositif de mise en marche d'une turbine à vapeur.

Elektrisches Generatoraggregat

Moteur à combustion interne à pistons suralimenté

Verbrennungsturbinen-Kraftanlage.

Einrichtung zum Anfahren von Turbinen

Verfahren und Vorrichtung zur Steuerung eines Anfahr-Schnellschlussventils

Verfahren und Vorrichtung zum automatischen Steuern von Maschinen und Verwendung der Steuervorrichtung

Einrichtung zum langsamen Anwärmen der Gehäuse von Dampfturbinen

Verfahren und Einrichtung zum raschen Anfahren und zur Regelung con Dampfturbinen.

Vorrichtung zum Betriebsbereithalten und Schnellstarten von Dampfturbinen

Einrichtung zur raschen Inbetriebnahme und Belastung von Dampfturbinen.

Verfahren für das automatische Anfahren und für den sicheren Betrieb von Turbinen, insbesondere Dampfturbinen

Für den nachträglichen Anbau und für einen vollautomatischen Betrieb geeignete Wellendrehvorrichtung für Dampf- oder Gasturbinen mit Freilaufkupplung

Einrichtung für das selbsttätige Anfahren sowie für das Belasten von Dampfturbinen

Beschleunigungsregler für eine Gasturbine

Dampfkraftanlage mit aufgeladenem Dampferzeuger

Anfahreinrichtung für einen an eine Turbine angekuppelten Generator

Verfahren zur automatischen Steuern von Turbomaschinen sowie automatische Steuervorrichtung und deren Verwendung

Steuereinrichtung für Dampfturbinen

Regelung einer Dampfturbinenanlage mit Zwischenüberhitzung

Einrichtung für automatisches Anlassen und Abstellen von Dampf- und Gasturbinen, insbesondere von Gegendruckdampfturbinen

Verfahren zur automatischen Ingangsetzung von Turbinenaggregaten, insbesondere von Gasturbinen, und Einrichtung zur Durchführung des Verfahrens

Kraftanlage mit mindestens je einer Gasturbine und einer Dampfturbine

Verfahren zur Herstellung von 6-Alkoxy-Pyridaziniumverbindungen

Steam turbine control arrangement and method for controlling a steam turbine

In the starting and in load changes of the steam turbine two methods of feeding steam into the first turbine stage are possible. Either all valves (7-10) of the nozzle arcs (37-40) are operated simultaneously over the entire nozzle ring (full-arc admission) or steam is admitted to the individual nozzle arcs (37-40) in succession by individual operation of the valves (7-10) (partial-arc admission). In order to substantially reduce the thermal stresses in the turbine rotor, a system of control is implemented in such a way that on the basis of a plurality of turbine parameters, the two methods of steam feed (partial-arc admission and full-arc admission) are suitably combined. ...

Safety device for optimum, automatic determination of the beginning of the starting process in turbo systems

Starter control device to be associated with speed regulators for main turbines

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

compressor starting drain systemcompressor starting drain system for a turbine system and method for controlling a.

Ein Verdichterstartablasssystem für ein Turbinensystem weist einen Verdichterabschnitt (12) auf. Weiter ist ein Turbinenabschnitt (24) vorhanden, der stromabwärts des Verdichterabschnitts (12) angeordnet ist. Darüber hinaus ist wenigstens ein Kanal (42) vorhanden, der mit dem Verdichterabschnitt (12) strömungsmässig verbunden ist, wobei der wenigstens eine Kanal (42) dazu eingerichtet ist, eine Startablassentnahme von dem Verdichterabschnitt (12) zu einer Stelle stromabwärts des Turbinenabschnitts (24) zu leiten. Noch weiter ist wenigstens eine Steuerungsvorrichtung (50) des wenigstens einen Kanals (42) vorhanden, die dazu eingerichtet ist, die Startablassentnahme während eines Teildrehzahlbetriebs des Turbinensystems aktiv anzupassen.

Turbo-'s group with starting device.

Die Erfindung betrifft eine Turbogruppe (100) mit Anfahrvorrichtung (120). Die Turbogruppe umfasst einen Verdichter (102), eine Brennkammer (103) und eine Turbine (104), die entlang eines Strömungspfades der Turbogruppe angeordnet sind. Die Anfahrvorrichtung (120) dient zum Anfahren der Turbogruppe und umfasst einen Dampferzeuger (121) zur Erzeugung von unter Überdruck stehendem Dampf und eine Zuführleitung (125) zur Zuführung des Dampfes in den Strömungspfad (101) der Turbogruppe (100). Ferner betrifft die Erfindung ein Verfahren zum Anfahren der Turbogruppe. Das Verfahren umfasst, unter Überdruck stehenden Dampf zu erzeugen und den Dampf in den Strömungspfad der Turbogruppe zuzuführen.

Procedure for the operation of a combination power station.

Bei einem Verfahren zum Betreiben eines Kombikraftwerke, welches eine Gasturbinenanlage (11) und einen mit der Gasturbinenanlage (11) über einen Abhitzedampferzeuger (24) verbundenen, wenigstens eine Dampfturbine (23) aufweisenden Wasser-Dampf-Kreislauf aufweist. Die Gasturbinenanlage (11) umfasst einen Verdichter (13), eine Brennkammer und eine Turbine (16). Zur Kühlung der Turbine (16) wird am Verdichter (13) verdichtete Luft abgenommen und in wenigstens einem von Wasser durchflossenen Kühler (18, 19) unter Erzeugung von Dampf abgekühlt und in die Turbine (16) eingeführt. Mindestens bei laufender Gasturbinenanlage (11) vor dem oder beim Anfahren des Wasser-Dampf-Kreislaufs wird die Abhitze, die in dem im wenigstens einen Kühler (18, 19) erzeugten Dampf enthalten ist, innerhalb des Kombikraftwerkes zur Vorwärmung der Anlage nutzbringend eingesetzt.

Insert Piece for a Turbocharger

Die Erfindung betrifft ein Einsatzstück (1) als Berstschutzvorrichtung für einen Turbolader (10), insbesondere Radialturbolader, mit einem Turbinengehäuse (20), das ein in dem Turbinengehäuse (20) drehbar angeordnetes Turbinenrad (21) vollumfänglich umfasst, wobei die Berstschutzvorrichtung (1) um eine zentrale Achse (A) in Umfangsrichtung ringförmig an der Turbinengehäuseinnenwand (22) angeordnet ist, um das Turbinenrad (21) zumindest teilweise zu umgreifen, wobei die Berstschutzvorrichtung (1) wenigstens eine/n erste/n Aussparung/Hohlraum (2) aufweist, wobei diese/r Aussparung/Hohlraum (2) in der Berstschutzvorrichtung (1) so ausgebildet ist, dass die kinetische Energie von Bruchstücken des Turbinenrads (21) bei dessen Zerbersten durch die Berstschutzvorrichtung (1) aufgrund plastischen Verformens der/des Aussparung/Hohlraums (2) aufgenommen wird und dazu die/der erste Aussparung/Hohlraum (2) einseitig in Richtung des Turbinengehäuses (20) geöffnet ist.

Method for starting a combustion system

Device of starting to steam turbine in an installation of gas turbine

GAS GENERATOR AND TURBINE ENGINE EQUIPPED WITH SUCH GENERATOR FOR STARTING

Process and fast device of starting and Re? lage of steam turbines

PROCEDE ET SYSTEME DE COMMANDE D'UNE TURBINE A VAPEUR

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

GAS TURBINE ENGINE STARTER HAS ENGAGED WITH A LOW PRESSURE

METHOD AND SYSTEM FOR STARTING TRUST TURBOMACHINE

METHOD FOR MONITORING A DEGREE OF CLOGGING OF INJECTORS FOR STARTING A TURBO ENGINE

Method for checking proper closure of oil pressurizing valve in aircraft turboshaft engine oil circuit, involves comparing measured time with nominal time, and stating valve defective closure when measured time is greater than nominal time

Procédé pour la vérification de la bonne fermeture d'un clapet de surpression (3) monté, sur la canalisation d'alimentation (11) du circuit d'huile d'une turbomachine, en aval de la pompe d'alimentation, ledit circuit comportant au moins une vanne (6) de régulation de la température d'huile de retour apte à se déplacer sous l'effet d'une consigne de mise en mouvement, et une canalisation de pressurisation (13) pour assurer la mise en mouvement de ladite vanne (6) alimentée par un piquage sur la canalisation d'alimentation (11) entre ladite pompe d'alimentation (2) et ledit clapet (3), la position de la vanne de régulation (6) étant en outre mesurée en continu par un capteur de position, caractérisé en ce qu'il comprend les étapes suivantes : - envoi à la vanne de régulation (6) d'une consigne de déplacement vers sa position d'ouverture, - mesure du temps mis par la vanne pour atteindre la pleine ouverture, - comparaison de ce temps au temps nominal, hors état de panne du clapet, et - déclaration ...

STARTER/ALTERNATOR CONSTANT FREQUENCY FOR AIRCRAFT ENGINE

Démarreur/alternateur (55) à fréquence constante pour moteur à turbine, comportant un premier onduleur/convertisseur (56), un second onduleur/convertisseur (60), une liaison de c.c. (58) connectant électriquement le premier onduleur/convertisseur (56) au second onduleur/convertisseur (60), et une machine électrique ayant une machine principale synchrone, le démarreur/alternateur (55) à fréquence constante pouvant fonctionner en mode démarrage et en mode génération.

LUBRICATION DEVICE OF AN EPICYCLIC REDUCTION GEAR COMPATIBLE MODULAR ASSEMBLY.

PNEUMATIC DEVICE FOR FAST WAKE-UP OF A GAS TURBINE ENGINE, SYSTEM ARCHITECTURE OF A HELICOPTER PROPELLANT MULTI-AND HELICOPTER CORRESPONDING

APPARATUS FOR CONTROLLING THE ACCELERATION OF A GAS TURBINE

RANKINE CYCLE START UP SYSTEM

ELECTRICITY GENERATING ARRANGEMENTS

Systems and methods for controlling the startup of a gas turbine

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control a fuel flow provided to a combustor component associated with the gas turbine. A drive component may be configured to supply a rotational force to a shaft associated with the gas turbine. At least one control device may be configured to (i) direct the gas discharge component to discharge gas from the compressor component, (ii) direct the fuel control component to adjust the fuel flow, and (iii) direct the drive component to rotate the shaft.

System and method for warming up a steam turbine

A system for warming up a steam turbine includes a gas turbine and a controller operably connected to the gas turbine. The controller is programmed to receive a plurality of measured input signals and control the gas turbine to produce an exhaust having a desired energy. A first measured input signal is reflective of a measured operating parameter of the gas turbine and a second measured input signal is reflective of an operating parameter of the steam turbine. A method for warming up a steam turbine includes sending a plurality of measured input signals to a controller, wherein a first measured input signal reflects a measured operating parameter of a gas turbine and a second measured input signal reflects an operating parameter of the steam turbine. The method further includes controlling the gas turbine based on the plurality of measured input signals and producing an exhaust from the gas turbine, wherein the exhaust has a desired energy.

Methods and systems for turbine line replaceable unit fault detection and isolation during engine startup

Systems and methods for isolating a performance anomaly within one or more line replaceable units (LRUs) on a gas turbine engine by monitoring the start up transient are presented. The system comprises a set of sensors, an anomaly detector and a fault isolation reasoner. Each sensor of the set monitors at least one operating parameter of at least one engine component. The anomaly detector is configured to detect an anomaly in a component by comparing a particular value of an operating parameter to a base line value of that parameter. The specific cause of the startup anomaly is isolated utilizing a set of component reasoners that is based on the nature of the detected anomaly. The key events during the engine startup are identified by the combination of monitoring physically relevant phases of a startup and monitoring the engine control schedule. The values at these key events are used for comparing at the anomaly detector.

PUMP, PUMP SYSTEM, METHOD OF CONTROLLING PUMP, AND COOLING SYSTEM

A pump includes: an impeller that moves fluid; a housing section, provided adjacent to a channel for the fluid, that communicate with the channel; and a controller that positions the impeller in the channel during a driving of the impeller and houses the impeller in the housing section during a stoppage of driving of the impeller. 1. A pump comprising:an impeller that moves fluid;a housing section, provided adjacent to a channel for the fluid, that communicate with the channel; anda controller that positions the impeller in the channel during a driving of the impeller and houses the impeller in the housing section during a stoppage of driving of the impeller.2. The pump according to claim 1 , further comprising claim 1 ,an electromagnet section provided in a location opposite to the housing section such that the channel is disposed therebetween,wherein the impeller includes a magnetic element controlled by the electromagnet section.3. The pump according to claim 2 , wherein the controller energizes the electromagnet section and positions the impeller in the channel during the driving of the impeller claim 2 , and the controller stops energizing the electromagnet section and houses the impeller in the housing section during the stoppage of driving of the impeller.4. The pump according to claim 2 , wherein the impeller includes a permanent magnet as the magnetic element.5. The pump according to claim 2 , wherein the controller positions the impeller in the channel using attraction of the magnetism of the electromagnet section during the driving of the impeller claim 2 , and the controller houses the impeller in the housing section using repulsion of the magnetism of the electromagnet section during the stoppage of driving of the impeller.6. The pump according to claim 2 , further comprising claim 2 ,a motor that rotates the electromagnet section,wherein the controller positions the impeller in the channel during a driving of the motor, and the controller houses the ...

Method for starting a turbomachine

A method of starting a turbine engine, including a re-try performed if a main injector has not ignited when a shaft has reached a first predetermined speed value, the re-try including: a stopping during which a starter and the ignitor device are stopped; a second ignition during which fuel is injected into the combustion chamber, the ignitor device being actuated, the second ignition being performed when a speed of rotation of the shaft reaches a second predetermined speed value; and a second starting during which the starter is actuated once more to drive the shaft in rotation.

Neural network-based turbine monitoring system

A neural network-based system for monitoring a turbine compressor. In various embodiments, the neural network-based system includes: at least one computing device configured to monitor a turbine compressor by performing actions including: comparing a monitoring output from a first artificial neural network (ANN) about the turbine compressor to a monitoring output from a second, distinct ANN about the turbine compressor; and predicting a probability of a malfunction in the turbine compressor based upon the comparison of the monitoring outputs from the first ANN and the second, distinct ANN.

SYSTEM AND METHOD FOR PROVIDING END-USE SPECIFIC CUSTOMIZATION OF GAS TURBINE ENGINE OPERATION

A system and method provide aircraft-specific customization of gas turbine engine operation. The system includes a gas turbine engine, a first processing unit, and an engine controller. The first processing unit is configured to selectively transmit an activation key. The engine controller is in operable communication with the first processing unit and the gas turbine engine. The engine controller is configured to receive the activation key transmitted by the first processing unit and is operable, upon receipt of the activation key, to: verify the received activation key is correct, enable operational parameters in the gas turbine engine and the engine controller when the received activation key is correct, and control the gas turbine engine using the enabled operational parameters. 1. A system for providing end-use specific customization of gas turbine engine operation , the system comprising:a gas turbine engine;a first processing unit configured to transmit an activation key, the activation key having one or more operational parameters associated therewith; and verify the received activation key is correct by comparing the received activation key to one or more known-to-be-valid activation keys,', 'enable the one or more operational parameters associated with the activation key in the gas turbine engine and the engine controller when the received activation key is correct, and', 'control the gas turbine engine using the enabled operational parameters., 'an engine controller in operable communication with the first processing unit and the gas turbine engine, the engine controller configured to receive the activation key transmitted by the first processing unit and operable, upon receipt of the activation key, to2. The system of claim 1 , further comprising:a controller memory storage unit disposed within the engine controller, the controller memory storage unit having at least one known-to-be-valid activation key stored therein.3. The system of claim 1 , further ...

COMPRESSED AIR ENERGY STORAGE POWER GENERATION APPARATUS AND COMPRESSED AIR ENERGY STORAGE POWER GENERATION METHOD

A compressed air energy storage power generation device includes motors, compressors that compress air, an accumulator tank that accumulates compressed air, expanders to driven by the compressed air supplied from the accumulator tank, generators, and a control device that controls driving of the motors. The control device includes a power supply command receiver that receives a power supply command, a priority setting unit that sets priority to the motors so that the motor whose elapsed time from stop is shorter has higher priority, a number-of-units determination unit that determines the number of the motors to be driven on the basis of an amount of input power indicated by the power supply command, and a drive unit that drives the motors in the descending order of the priority until the number of the driven motors becomes equal to the number of motors to be driven determined by the number-of-units determination unit. 1. A compressed air energy storage power generation device , comprising:a plurality of motors driven by input power;a plurality of compressors driven by the motors, respectively, to compress air;an accumulator tank configured to accumulate compressed air compressed by the compressors;an expander driven by the compressed air supplied from the accumulator tank;a generator driven by the expander to supply output power to a supply destination; anda control device configured to control driving of the motors, whereinthe control device includesa power supply command receiver configured to receive a power supply command indicating an amount of the input power before the input power is supplied,a priority setting unit configured to set priority to the motors so that the motor whose elapsed time from stop is shorter has higher priority,a number-of-units determination unit configured to determine the number of the motors to be driven on the basis of the amount of the input power indicated by the power supply command, anda drive unit configured to drive the ...

Combined cycle power plant and method for operating such a combined cycle power plant

The invention relates to a combined cycle power plant including a gas turbine the exhaust gas outlet of which is connected to a heat recovery steam generator, which is part of a water/steam cycle, whereby, for having a large power reserve and at the same time a higher design performance when operated at base load, the gas turbine is designed with a steam injection capability for power augmentation. For having a large power reserve at improved and optimized design performance when the plant is being operated at base load, the gas turbine includes at least one combustor, and a compressor for providing cooling air for that gas turbine, which is extracted from the compressor and cooled down in at least one cooling air cooler. The steam for steam injection is generated in said cooling air cooler, whereby said steam is injected into an air side inlet or outlet of said cooling air cooler and/or directly into said at least one combustor. The heat recovery steam generator is equipped with a supplementary firing, which is at least a single stage supplementary firing to increase the high pressure steam production and providing augmentation power as power reserve to a grid when required.

SYSTEM AND METHODS FOR CONTROLLING SURGE MARGIN IN THE COMPRESSOR SECTION OF A GAS TURBINE ENGINE

Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. A first compressor section and a second compressor section are in fluid communication with a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit is controlled by bypass control valves. 1. A system for controlling surge margin in a compressor section of a gas turbine engine , the system comprising: one or more compressor stages defining a first compressor section flowpath; and', 'a first compressor section discharge in fluid communication with the first compressor section flowpath;, 'a first compressor section comprisinga first compressor section bypass port positioned along the first compressor section and in fluid communication with the first compressor flowpath; one or more compressor stages defining a second compressor section flowpath, the second compressor section flowpath in fluid communication with the first compressor section flowpath; and', 'a second compressor section discharge in fluid communication with the second compressor section flowpath;, 'a second compressor section comprisinga second compressor section bypass port positioned along the second compressor section and in fluid communication with the second compressor section flowpath;a bypass conduit, extending between the first compressor section bypass port and the second compressor section bypass port;a first compressor section bypass control valve positioned in the bypass conduit downstream of the first compressor section bypass port;a second compressor section bypass control valve positioned in the bypass conduit downstream of the second compressor section bypass port;an auxiliary turbine positioned in the bypass conduit between the first compressor section bypass control valve and the second compressor section bypass control valve;a discharge conduit coupled to and in fluid ...

GAS TURBINE ENGINE ELECTRICAL GENERATOR

An aircraft gas turbine engine () comprises a main engine shaft (), a main engine shaft bearing arrangement () configured to rotatably support the main engine shaft () and an electric machine () comprising a rotor () and a stator (). The rotor () is mounted to the main engine shaft () and is rotatably supported by the main engine shaft bearing arrangement (), and the stator () is mounted to static structure () of the gas turbine engine (). 1. An aircraft gas turbine engine comprising:a main engine shaft;a main engine shaft bearing arrangement configured to rotatably support the main engine shaft; andan electric machine comprising a rotor and a stator; whereinthe rotor is mounted to the main engine shaft and is rotatably supported by the main engine shaft bearing arrangement, and the stator is mounted to static structure of the gas turbine engine.246. A gas turbine engine according to claim 1 , wherein the stator of the electric machine is cantilevered from the static structure () of the gas turbine engine.332. A gas turbine engine according to claim 2 , wherein the electric machine stator () is mounted by a mount member extending generally rearward or generally forward from a gas turbine engine static structure.4. A gas turbine engine according to claim 1 , wherein the main engine shaft comprises a radially inner portion and a radially outer portion separated by an annular space claim 1 , and joined at one end.5. A gas turbine engine according to claim 4 , wherein the electric machine rotor is mounted to the radially outer portion of the main engine shaft6. A gas turbine engine according to claim 5 , wherein the radially inner and radially outer portions may be joined by a fusible connector.7. A gas turbine engine according to claim 1 , wherein the main shaft bearing arrangement comprises a first bearing and a second bearing claim 1 , wherein the first bearing may comprise a radial load bearing claim 1 , and the second bearing may comprise a thrust bearing.8. A gas ...

METHOD FOR COUPLING TWO SUB-SHAFTS

A method for coupling a first sub-shaft, which has a first turbomachine and a generator connected to a mains supply, to a second sub-shaft, which has a second turbomachine, by means of an overrunning clutch, has the following steps: a) rotating the second sub-shaft with a starting rotational speed which is lower than the rotational speed of the first sub-shaft; b) measuring the mains frequency of the mains supply; c) measuring a differential angle between the first sub-shaft and the second sub-shaft; d) accelerating the second sub-shaft with an acceleration value which is produced using the mains frequency measured in step b), the differential angle and the starting rotational speed, and therefore the overrunning clutch couples the two sub-shafts to each other with a previously determined target coupling angle. 1. A method for coupling a first sub-shaft , which has a first fluid-flow machine and a generator connected to a mains supply , to a second sub-shaft , which has a second fluid-flow machine , by means of an overrunning clutch , comprising the steps:a) rotating the second sub-shaft with an initial rotational speed which is lower than the rotational speed of the first sub-shaft;b) measuring the mains frequency of the mains supply;c) measuring a differential angle between the first sub-shaft and the second sub-shaft;d) accelerating the second sub-shaft with an acceleration value which is produced by using the mains frequency measured in step b), the differential angle and the initial rotational speed, so that the overrunning clutch couples the two sub-shafts to each other with a previously determined target coupling angle;e) measuring a new mains frequency during the accelerations of the second sub-shaft;f) in the event that the new mains frequency is different from the mains frequency measured in step b), accelerating the second sub-shaft with a changed acceleration value, which is produced by using the new mains frequency.2. The method as claimed in claim 1 , ...

PRE-START MOTORING SYNCHRONIZATION FOR MULTIPLE ENGINES

An aspect includes a system for pre-start motoring synchronization for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to synchronize a motoring time of the first engine starting system with one or more other engine starting systems of one or more other engines of the aircraft by extending the motoring time of the first engine starting system to match, within a synchronization tolerance, the motoring time of the one or more other engine starting systems in a pre-start motoring sequence. 1. A system for pre-start motoring synchronization for multiple engines of an aircraft , the system comprising:a first engine starting system of a first engine; anda controller operable to synchronize a motoring time of the first engine starting system with one or more other engine starting systems of one or more other engines of the aircraft by extending the motoring time of the first engine starting system to match, within a synchronization tolerance, the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.2. The system as in claim 1 , wherein the motoring time of the first engine starting system is synchronized with the one or more other engine starting systems by comparing an initial value of the motoring time of the first engine starting system with an initial value of the motoring time of the one or more other engine starting systems and selecting a largest value as the motoring time for the first engine starting system and the one or more other engine starting systems.3. The system as in claim 2 , wherein the controller provides the initial value of the motoring time of the first engine starting system to one or more other controllers and receives the initial value of the motoring time of the one or more other engine starting systems from the one or more other controllers.4. The system as in claim 2 , wherein the controller maintains ...

CROSS ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING

A system is provided for cross engine coordination during gas turbine engine motoring. The system includes a first gas turbine engine of a first engine system, a first air turbine starter of the first engine system, a first starter air valve of the first engine system, and a controller. The controller is operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data. 1. A system for cross engine coordination during gas turbine engine motoring , the system comprising:a first gas turbine engine of a first engine system;a first air turbine starter of the first engine system;a first starter air valve of the first engine system; anda controller operable to command the first starter air valve to control delivery of compressed air to the first air turbine starter during motoring of the first gas turbine engine, monitor cross engine data of a second gas turbine engine of a second engine system to detect a present condition or a commanded action that modifies an aspect of the compressed air received at the first starter air valve, and command an adjustment to the first engine system to compensate for the modified aspect of the compressed air based on the cross engine data.2. The system as in claim 1 , wherein the compressed air is driven by an auxiliary power unit of the aircraft claim 1 , a ground cart claim 1 , or a cross engine bleed.3. The system as in claim 1 , wherein the controller commands the first starter air valve based on one or more of: an engine speed of a starting spool of the first gas turbine ...

AIR SUPPLY CONTROL DURING MOTORING OF A GAS TURBINE ENGINE

A system for motoring a gas turbine engine of an aircraft is provided. The system includes an air turbine starter, a starter air valve operable to deliver compressed air to the air turbine starter, and a controller. The controller is operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition. 1. A system for motoring a gas turbine engine of an aircraft , the system comprising:an air turbine starter;a starter air valve operable to deliver compressed air to the air turbine starter; anda controller operable to control motoring of the gas turbine engine, detect a fault condition that prevents the controller from maintaining a motoring speed below a threshold level, and command a mitigation action that reduces delivery of the compressed air to the air turbine starter based on detection of the fault condition.2. The system as in claim 1 , wherein the compressed air is driven by an auxiliary power unit of the aircraft.3. The system as in claim 2 , wherein the controller relays the command for the mitigation action to the auxiliary power unit through an engine control interface using a digital communication bus.4. The system as in claim 3 , wherein the mitigation action comprises opening one or more bleed valves to purge the compressed air.5. The system as in claim 4 , wherein the controller receives state information of the one or more bleed valves through the engine control interface.6. The system as is claim 1 , wherein the mitigation action comprises shutting one or more supply valves of the compressed air.7. The system as in claim 1 , wherein the fault condition comprises a stuck open position of the starter air valve.8. The system as in claim 1 , wherein the fault condition comprises a pressure surge of the compressed ...

Start-Up Control Device and Start-Up Control Method for Power Plant

To provide a start-up control device and a start-up control method for a power plant capable of changing the start-up completion estimated time to a desired time simply and safely while starting the power plant. The start-up control device includes an equipment state quantity acquisition unit acquiring an equipment state quantity of the power plant, a start-up schedule calculation unit calculating a current start-up schedule based on the equipment state quantity and a first thermal stress limiting value and calculating a start-up schedule changing plan based on the equipment state quantity and a second thermal stress limiting value, an equipment operation amount calculation unit calculating an equipment operation amount of the power plant based on the current start-up schedule, a screen display unit displaying respective start-up completion estimated times of the current start-up schedule and the start-up schedule changing plan, and an instruction input unit instructing the start-up schedule calculation unit to perform switching from the current start-up schedule to the start-up schedule changing plan.

STARTER/GENERATOR

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space. 1. A gas turbine engine comprising:a high pressure spool and a low pressure spool, the low pressure spool including a low pressure shaft operably connected to a fan, the high pressure spool including a high pressure shaft operably connected to a high pressure turbine, the low pressure shaft and the high pressure shaft being co-axial with one another;a rotor of an electric starter generator coupled to the high pressure shaft;a stator disposed radially outward of the rotor;a high pressure shaft bearing;a forward strut supporting the high pressure shaft bearing; anda plurality of conductors electrically coupled to the stator and extending radially through the forward strut to an outer casing of the gas turbine engine.2. The gas turbine engine of claim 1 , wherein the plurality of conductors comprise a first plurality of conductors claim 1 , further comprising a second plurality of conductors electrically coupled between the rotor and the first plurality of conductors claim 1 , wherein the second plurality of conductors extend substantially axially.3. The gas turbine engine of claim 2 , further comprising a pin connector connecting conductors of the first plurality of conductors and conductors of the second plurality of conductors.4. The gas turbine engine of ...

Air turbine starter

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine. A screen is located within the interior between the at least one turbine member and the set of outlets and adapted to mitigate ejection of ignited particles from within the housing.

SYSTEM AND METHOD FOR ROTATING A GAS TURBINE ENGINE DURING A MOTORING CYCLE

Systems and methods for rotating a gas turbine engine during a motoring cycle are provided. The system may comprise a controller in electronic communication with an auxiliary power unit (APU), a starter air valve, and a gas turbine engine. The APU may supply compressed air to the starter air valve which may supply the compressed air to an engine starter in mechanical communication with the engine. The rotational speed of the engine may be controlled by the engine starter based on the pressure of the compressed air received from the starter air valve. The controller may be configured to control airflow and air pressure through the system, by modulating the airflow from the APU and/or from the starter air valve. 1. A system , comprising:a sensor configured to measure a rotational speed of the gas turbine engine;a controller in electronic configuration with a starter air valve, an auxiliary power unit (APU), and the sensor; and receiving, by the controller, the rotational speed of the gas turbine engine from the sensor;', 'transmitting, by the controller, an APU command to the APU, wherein the APU command is based on the rotational speed of the gas turbine engine and is configured to control a pressure of the supply airflow to the starter air valve; and', 'transmitting, by the controller, a starter air valve command to the starter air valve, wherein the starter air valve command is based on the engine sensor feedback and is configured to control an output pressure of the airflow to the engine starter., 'a tangible, non-transitory memory configured to communicate with the controller, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising2. The system of claim 1 , wherein the operations further comprise the step of controlling claim 1 , by the controller claim 1 , a speed of rotation in the gas turbine engine by modulating the output pressure of the ...

METHOD FOR OPERATING AN ELECTRIC UNIT FOR A PUMPED-STORAGE POWER PLANT

A pump-storage power plant, such as an electric unit, for this purpose can include a rotating electric synchronous machine and a frequency converter as well as a method for operating the electric unit. An exemplary method provides that the frequency converter is used to start the turbine and an output of the electric machine is fed directly into the current network after start-up, for example. Another exemplary method provides that the frequency converter is used to start the pump and the pump is started directly from rest and under load of a flooded pump or a water column, for example. Another exemplary method provides that the electric machine is synchronised with a frequency of the current network and is operated synchronously with the current network independent of the operating state of the pump or the turbine and supplies active power and reactive power. 1. A method for operating an electric unit for a pumped-storage power plant , wherein the electric unit includes a rotating electric synchronous machine and a frequency converter , wherein the frequency converter is connected to a stator of the synchronous machine , and wherein the synchronous machine is connected to a turbine and to an electric grid via the frequency converter , the method comprising:running up the turbine from standstill by generating a current flow in the electric grid via the frequency converter with continuous conversion of a frequency of the synchronous machine in an entire speed range of the turbine into a frequency of the electric grid.2. A method for operating an electric unit for a pumped-storage power plant , wherein the electric unit includes a rotating electric synchronous machine and a frequency converter , wherein the frequency converter is connected to a stator of the machine , and wherein the synchronous machine is connected to a pump and to an electric grid via the frequency converter , the method comprising:running up the pump from standstill by generating a current flow in ...

ENERGY RECOVERY FOR HIGH POWER PUMPING SYSTEMS AND METHODS USING EXHAUST GAS HEAT TO GENERATE THERMOELECTRIC POWER

Embodiments of a power generation system and methods to be used in conjunction with a high-powered turbine engine are disclosed. The power generation system includes a turbine engine having an exhaust diffuser section installed on the exhaust duct of the turbine engine and a turbine engine exhaust stack assembly connected to the turbine engine exhaust diffuser section. An embodiment further includes thermo-electric generator (TEGs) sub-assemblies connected to the turbine engine exhaust stack assembly. In other embodiments electrical storage devices such as batteries are used. 1. A hydraulic fracturing power generation system positioned onboard a hydraulic fracturing trailer assembly , the system comprising: (a) a turbine engine mounted to the hydraulic fracturing trailer assembly,', '(b) a reduction gear box connected to the turbine engine and mounted to the hydraulic fracturing trailer assembly,', '(c) a drive shaft connected to the reduction gear box and mounted to the hydraulic fracturing trailer assembly, and', '(d) a turbine engine exhaust diffuser section mounted to the hydraulic fracturing trailer assembly and connected to the turbine engine;, 'a high power hydraulic fracturing generation assembly includinga reciprocating plunger pump connected to the drive shaft and mounted to the hydraulic fracturing trailer assembly; and (a) a turbine engine exhaust stack assembly mounted to the hydraulic fracturing trailer assembly and connected to the turbine engine exhaust diffuser section,', '(b) a set of thermo-electric generator (TEG) sub-assemblies connected to the turbine engine exhaust stack assembly to generate electric power responsive to the turbine engine exhaust stack assembly, and', '(c) a power storage and distribution source mounted to the hydraulic fracturing trailer assembly to store and distribute power generated from the set of TEG sub-assemblies across the hydraulic fracturing trailer assembly., 'a thermoelectric power generation assembly mounted to ...

Air turbine starter

An air turbine starter for starting an engine includes a starter housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet. A turbine section is located within the starter housing and includes a turbine member having a central disk and a set of airfoils spaced circumferentially about the central disk, as well as a sealing structure located within the starter housing.

Apparatus and method for servicing gas turbine engines

The present disclosure relates to an apparatus having an elongated body configured to be inserted into a tubular structure extending between a first combustor and a second combustor of a gas turbine engine. A movable arm may be positioned proximate to a first end of the elongated body, and the movable arm may be configured to engage a surface of the first combustor when the elongated body is placed within the tubular structure. A drive member may be accessible near a second end of the elongated body, and the drive member may be configured to rotate within the elongated body and to drive the movable arm along a longitudinal axis of the elongated body toward the second end to separate the tubular structure from the second combustor.

Aircraft engine constant frequency starter/generator

A constant frequency starter/generator for a turbine engine includes a first inverter/converter, a second inverter/converter, a DC link electrically connecting the first inverter/converter to the second inverter/converter, and an electric machine having a synchronous main machine, wherein the constant frequency starter/generator is operable in a start mode and a run mode.

Gas Turbine Combustion System

The present invention provides a gas turbine combustion system capable of minimizing unburned content of a gas fuel under all load conditions from partial load to rated load. A gas turbine combustion system includes: a plurality of gas fuel burners 32, 33; an IGV 9 that adjusts a flow rate of air to be mixed with a gas fuel; and a control system 500 that temporarily reduces an air flow rate from a reference flow rate to a set flow rate by outputting a signal to the IGV 9 when a combustion mode is switched from a partial combustion mode in which the gas fuel is burned with part of the gas fuel burners 32, 33 to a full combustion mode in which the gas fuel is burned with all of the gas fuel burners 32, 33.

A METHOD FOR STARTING UP A GAS TURBINE ENGINE OF A COMBINED CYCLE POWER PLANT

The invention relates to a method for starting up a gas turbine engine of a combined cycle power plant. The method includes applying load to the gas turbine engine and increasing the load until a predetermined combustor firing temperature is reached, while keeping the adjustable inlet guide vanes in a start position adapted to reduce the mass flow of air into the compressor; further increasing the load of the gas turbine engine while opening the adjustable inlet guide vanes and keeping the predetermined combustor firing temperature constant until the inlet guide vanes reach an end position adapted to increase the mass flow of air into the compressor; further increasing the load of the gas turbine engine while keeping the adjustable inlet guide vanes in the end position until a predetermined load of the gas turbine engine is reached. 1. A method for starting up a gas turbine engine of a combined cycle power plant , the gas turbine engine including a compressor , a combustor and a turbine , the compressor providing compressed air to the combustor for combustion with a fuel to produce a working fluid and the turbine receiving the working fluid to produce power; the compressor comprising adjustable inlet guide vanes , the adjustable inlet guide vanes being adjustable between a fully closed position for minimizing the mass flow of air into the compressor and a fully open position for providing the maximum mass flow of air into the compressor wherein the method comprises the steps of:step 1: applying load to the gas turbine engine and increasing the load until a predetermined combustor firing temperature is reached, while keeping the adjustable inlet guide vanes in a start position adapted to reduce the mass flow of air into the compressor, whereby the predetermined combustor firing temperature is chosen to be an emission-compliant temperature,step 2: further increasing the load of the gas turbine engine while opening the adjustable inlet guide vanes and keeping the ...

Systems and Methods for Proactive Operation of Process Facilities Based on Historical Operations Data

Provided are techniques for proactively operating gas-oil separation plant (GOSP) type process facilities that include determining historical operational characteristics of a GOSP for a past time interval using historical operational data for the GOSP, determining expected operating characteristics of the GOSP for a subsequent time interval using the historical operational characteristics, determining an operating plan for the GOSP using the expected operating characteristics, and operating the GOSP in accordance with the operating plan. 1. A method of operating a gas oil separation plant (GOSP) , the method comprising: oil production;', 'power consumption;', 'gas export;', 'crude export;', 'sour gas export;', 'natural gas liquids (NGL) export;', 'fuel gas consumption; and', 'energy key performance indicator (KPI);, 'obtaining operational data for the GOSP, the operational data indicative of operational characteristics of the GOSP observed over a historical time interval, the historical time interval comprising an interval of time preceding a given point in time, the operational characteristics comprising (a) for each month of the historical time interval, an average monthly value determined based on values of the operational characteristic over the month;', '(b) for each week of the historical time interval, an average weekly value determined based on values of the operational characteristic over the week; and', '(c) for each day of the historical time interval, a daily value determined based on a value of the operational characteristic for the day:, 'determining, based on the operational data, historical operational characteristics of the GOSP for the historical time interval, the historical operational characteristics comprising, for each of the operational characteristics (a) an expected next month value determined based on the average monthly values for the operational characteristic;', '(b) an expected next week value determined based on the average weekly ...

AIRCRAFT TURBINE ENGINE WITH PLANETARY OR EPICYCLIC GEAR TRAIN

Aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft (), means () for taking off power from said low-pressure shaft, and a fan () that is driven by said low-pressure shaft by means of a reduction gear (), said reduction gear comprising at least one first element () that is connected to said low-pressure shaft for conjoint rotation, at least one second element () that is connected to said fan for conjoint rotation, and at least one third element () that is connected to a stator casing of the turbine engine, characterised in that said at least one third element is connected to said stator casing by disengageable connection means (), and comprising at least one member that can move from a first position in which said at least one third element is fixedly connected to said stator casing into a second position in which said at least one third element is separated from said stator casing and is free to rotate about said longitudinal axis. 1. An aircraft turbine engine comprising a low-pressure spool that comprises a low-pressure shaft that connects a rotor of a low-pressure compressor to a rotor of a low-pressure turbine , and a high-pressure spool that comprises a high-pressure shaft that connects a rotor of a high-pressure compressor to a rotor of a high-pressure turbine , the low-pressure and high-pressure shafts extending along the same longitudinal axis (A) , the turbine engine further comprising means for taking off power from said low-pressure shaft , and a fan that is driven by said low-pressure shaft by means of a planetary or epicyclic reduction gear , said reduction gear comprising at least one first element that is connected to said low-pressure shaft for conjoint rotation , at least one second element that is connected to said fan for conjoint rotation , and at least one third element that is connected to a stator casing of the turbine engine , characterised in that said at least one third element is connected to said ...

GAS TURBINE ENGINE COMPRISING A STARTER ENGAGED WITH A LOW-PRESSURE BODY

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body , a high-pressure rotating body, and a starter to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body , for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter. 1. Multi-spool gas turbine engine ( comprising: at least one rotating low-pressure body , a rotating high-pressure body , and a starter motor , the starter motor being coupled to the low-pressure body , the engine further comprising a first disengageable coupling device which is interposed between the low-pressure body and the high-pressure body in order to rotatably connect the high-pressure body to the low-pressure body in order to make it possible to start up the engine the starter motor , wherein the first coupling device is designed so as to be movable between:a first position, in which the coupling device is engaged so that the low-pressure body drives the high-pressure body,a second position, in which the coupling device is disengaged once a speed of the low-pressure body falls below that of the high-pressure body.2. Turbine engine according to claim 1 , wherein the first coupling device is of the freewheel type.3. Turbine engine according to claim 2 , wherein the low-pressure body comprises a shaft that is mounted coaxially in or on a shaft of the high-pressure body claim 2 , the first freewheel coupling device being mounted between the shafts of the low-pressure and high-pressure bodies.4. Turbine engine according to either claim 2 , wherein the first coupling device comprises a free wheel having jamming elements.5. Turbine engine according to claim 1 , comprising a gearbox for driving accessory equipment of 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 ...

Exhaust Heat Recovery Device

An exhaust heat recovery device provided with a Rankine cycle, capable of achieving improvements in start-up performance of the Rankine cycle and an efficient operation (actuation) of the Rankine cycle. An exhaust heat recovery device that recovers and uses exhaust heat of an engine includes: a Rankine cycle including a heater , an expander , a condenser , and a pump ; a bypass flow passage that allows refrigerant to circulate while bypassing the expander ; a bypass valve that opens and closes the bypass flow passage ; and a control unit . When starting up the Rankine cycle , the control unit executes control to actuate the pump with the bypass valve open, and then to close the bypass valve when a parameter indicating the condensation capacity of the condenser becomes a predetermined value or more. 1. An exhaust heat recovery device comprising:a Rankine cycle in which a heater configured to heat and vaporize refrigerant by exhaust heat of an external heat source, an expander configured to generate power by expanding the refrigerant passed through the heater, a condenser configured to condense the refrigerant passed through the expander, and a pump configured to send the refrigerant passed through the condenser to the heater are disposed in a circulation passage of the refrigerant;a bypass flow passage that allows the refrigerant to circulate while bypassing the expander;a bypass valve that opens and closes the bypass flow passage; anda control unit that, when starting up the Rankine cycle, executes control to actuate the pump with the bypass valve open, and then to close the bypass valve when a parameter indicating condensation capacity of the condenser becomes a predetermined value or more.2. The exhaust heat recovery device according to claim 1 , further comprising:a pressure difference determining unit that determines a pressure difference between a high-pressure side and a low-pressure side of the Rankine cycle,wherein when starting up the Rankine cycle, the ...

GAS TURBINE COMBINED CYCLE FOR HIGH FLEXIBILITY

A combined cycle power generation plant has parallel, normally-independent power generation trains, each having a gas turbine in line with a heat recovery steam generator. In a “parked” or spinning reserve operational state, combustion is discontinued at the gas turbine of one power generation train, which is placed on a turning gear. Combustion at the other power train is reduced, preferably to a minimum emissions-compliant level (NOx, CO) of the gas turbine operated at low level combustion. A bypass duct with controllable dampers apportions exhaust from the operating gas turbine to the heat recovery steam generators of both power trains. This maintains an elevated temperature in both heat recovery steam generators and enables fast restart. 1. A combined cycle power plant , comprising:at least two gas turbines operable to combust fuel during operation and supplying torque to at least one electrical generator via a shaft, each of the gas turbines producing an exhaust flow during operation, the exhaust flow being coupled in a flow path to at least one of two or more heat recovery steam generators, each of the heat recovery steam generators being associated with a respective one of the gas turbines in a power train, the heat recovery steam generators producing steam from the exhaust flow of the gas turbines during operation for extraction of further energy by a steam turbine;operational controls configured to assume a low load operational state of the combined cycle power plant wherein an active one of the two or more gas turbines is operated at a predetermined low load level and another of the two or more gas turbines is substantially shut down;a bypass duct for defining a flow path for gas turbine exhaust from an outlet of one of the gas turbines in one of the power trains to an inlet of the heat recovery steam generators of the other power trains;wherein in the low load operational state, the bypass duct conveys a portion of the exhaust flow produced by the active ...

Method for starting a turbine engine in cold weather and system for starting a turbine engine

A method for starting a turbine engine in cold weather, including a starting system intended for rotating a drive shaft of the turbine engine. The method includes the following steps: a pre-starting step in which a first starting signal is generated to control the drive shaft in a first direction of rotation about a longitudinal axis and in a second opposite direction of rotation in an alternating manner; and a starting step in which a second starting signal is transmitted to the starting system in order for the latter to drive the drive shaft of the turbine engine in a normal direction of rotation and in which the drive shaft is rotated until a rotation speed that causes the turbine engine to start.

CASING POSITION ADJUSTMENT DEVICE

In a steam turbine including a rotor including a free side end fixed by a journal bearing (not illustrated) in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction, and a casing including a fixed side end fixed by the thrust bearing in the axial direction (rotor axial direction), a casing position adjustment device is configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion. The casing position adjustment device includes: a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; and actuators, which deform the low-pressure casing end plate so that the low-pressure casing end plate extends toward the free side in the axial direction. 115-. (canceled)16. A casing position adjustment device in a steam turbine including a rotor including a free side end fixed by a journal bearing in a radial direction and a fixed side end fixed by a thrust bearing in an axial direction , and a casing including a fixed side end fixed by the thrust bearing in the axial direction , the casing position adjustment device configured to adjust an axial position of the casing with respect to the rotor due to thermal expansion , the casing position adjustment device comprising:a low-pressure casing end plate, which is an end plate oriented to a free side in the axial direction in a low-pressure casing of the casing, and has a diaphragm shape deformable in the axial direction; andactuators, which deform the low-pressure casing end plate such that the low-pressure casing end plate extends toward the free side in the axial direction.17. A casing position adjustment device according to claim 16 , wherein the casing is fixed by anchor bolts on the fixed side in the axial direction with respect to the low-pressure casing end plate.18. A casing position adjustment device ...

Aircraft propulsion system having at least one anti-fire tank

A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations. 1. A propulsion system comprising:a nacelle which is substantially tubular around a longitudinal axis, defined by an inner wall extending from a front of the nacelle to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front of the nacelle to the rear of the nacelle,a turbojet comprising a fan and being situated internally of the inner wall of said nacelle,at least one tank containing an extinguishing fluid, being located inside said nacelle between the inner wall and the outer wall, anda network of pipes hydraulically connected to said at least one tank,wherein said at least one tank extends around the inner wall,wherein said at least one tank is of a form having at least one open torus portion in a plane perpendicular to the longitudinal axis.2. The propulsion system according to claim 1 , wherein said at least one tank extends angularly around the periphery of said nacelle so that the lower part of said at least one tank is above a horizontal plane tangent to a lower edge of said inner wall of said nacelle.3. The propulsion system according to claim 1 , wherein said at least one tank is situated in a ...

System and Method for Measuring Clearance Gaps Between Rotating and Stationary Components of a Turbomachine

Systems and methods for measuring the clearance gaps between rotating and stationary components of a turbomachine are provided. In one exemplary aspect, flexible and degradable sensing arrays that include a plurality of microwave sensors are utilized to sense the clearance gaps between rotating and stationary components of the turbomachine. Microwaves generated by a microwave generator are transmitted to the sensors. Upon rotation of the rotating components, the rotating components reflect the microwaves transmitted thereto. The microwave sensors capture the transmitted signal and also capture a reflected signal indicative of the transmitted signal reflected by the rotating components. The signals are then forwarded to a computing device for processing. The amplitude difference at the interference fringes between the superimposed signals is representative of the clearance gaps between the rotating and stationary components. After measuring the clearance gaps, the turbomachine may be operated and the degradable sensing array may be consumed. 1. A system , comprising:a turbomachine comprising a rotating component rotatable about an axis of rotation and a stationary component spaced from the rotating component by a clearance gap;a sensor attached to one of the stationary component and the rotating component;an electromagnetic wave generator in electrical communication with the sensor and configured to generate electromagnetic waves; and receive a transmitted signal from the sensor, wherein the transmitted signal is representative of the electromagnetic waves received by the sensor;', 'receive, as the rotating component is rotated about the axis of rotation, a reflected signal from the sensor, wherein the reflected signal is representative of the electromagnetic waves reflected by the rotating component;', 'determine a delta between an amplitude of the transmitted signal and an amplitude of the reflected signal of the transmitted signal and the reflected signal; and', ' ...

Method and apparatus for estimating internal state of thermal component

A method of estimating an internal state of a thermal component of the invention includes a measurement step of measuring state quantity of the thermal component, an analysis-condition creation step of creating an analysis condition, a data assimilation step of obtaining probability distribution of each temperature distribution and displacement distribution through data assimilation calculation using a contraction model, a measured value, and the analysis condition, a post-processing step of obtaining the internal state of the thermal component, an analysis step of obtaining solution vectors of the temperature distribution and the displacement distribution, and a contraction-model construction step of extracting a subspace characterizing a linear space of a vector set and constructing a contraction model using the subspace, wherein, in the data assimilation step, the probability distribution is calculated using the contraction model, and, in the analysis step and the contraction-model construction step, the contraction model is constructed.

Systems and Methods for Boundary Control During Steam Turbine Acceleration

Certain embodiments of the disclosure may include systems and methods for boundary control during steam turbine acceleration. According to an example embodiment, the method can include receiving an indication the turbine is in an initial acceleration phase; receiving speed control parameter data from a plurality of sensors; receiving boundary control parameter data from a plurality of sensors; providing a control valve configured for controlling steam flow entering the turbine; determining the control valve position based on received speed control parameter data; determining the control valve position based on received boundary control parameter data; adjusting at least one boundary control parameter to the at least one boundary control parameter limit during turbine startup, wherein the value of a speed control parameter is simultaneously adjusted based on the adjusted at least one boundary control parameter; and adjusting the control valve position based at least on determined parameter data. 1. A method for starting a turbine , the method comprising:receiving an indication the turbine is in an initial acceleration phase;receiving speed control parameter data from a plurality of sensors;receiving boundary control parameter data from a plurality of sensors;providing a control valve configured for controlling steam flow entering the turbine;determining the control valve position based on received speed control parameter data;determining the control valve position based on received boundary control parameter data;adjusting at least one boundary control parameter to the at least one boundary control parameter limit during turbine startup, wherein the value of a speed control parameter is simultaneously adjusted based on the adjusted at least one boundary control parameter; andadjusting the control valve position based at least on determined parameter data;2. The method of claim 1 , further comprising: comparing the determined control valve position based on received ...

Method for coupling a steam turbine and a gas turbine at a desired differential angle

A method and an associated arrangement for coupling a rotational device, particularly a steam turbine, and a shaft device, particularly a gas turbine, includes the following steps: 1) accelerating the rotational device up to an output rotational speed that is below the rotational speed of the shaft device; 2) detecting a differential angle between the shaft device and the rotational device; and 3) accelerating the rotational device with an acceleration value that is derived from the target rotational speed difference, which is formed as a function of the detected differential angle, the acceleration and a desired target coupling angle.

COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION METHOD AND COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION DEVICE

In a compressed air energy storage and power generation device, a compressed air energy storage and power generation method defines, as a reference storage value, a storage value indicating that a storage amount of air in an accumulator tank is in a predetermined intermediate state. At the reference storage value, at least one of a motor and a generator rotates at a rated rotation speed. When a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or less than the rated rotation speed. When the storage value indicating the current storage amount in the accumulator tank is smaller than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or more than the rated rotation speed and equal to or less than a maximum permissible rotation speed. 1. A compressed air energy storage and power generation method , comprising:driving an electric motor by fluctuating input power;compressing air by a compressor mechanically connected to the electric motor;storing the compressed air, which is supplied from the compressor, in an accumulator tank;driving an expander by the compressed air supplied from the accumulator tank; andgenerating power by a generator mechanically connected to the expander, whereinthe compressed air energy storage and power generation method comprises:defining, as a reference storage value, a storage value indicating that a storage amount of the air in the accumulator tank is in a predetermined intermediate state;at the reference storage value, controlling at least one of the electric motor and the generator to rotate at a rated rotation speed;when a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, controlling at least one of the electric motor and the generator to rotate at equal to or less than ...

COAXIAL STARTER / GENERATOR AND AIR TURBINE STARTER

A system for starting a turbine engine is provided. The system may comprise a gearbox, a first starter, and a second starter. The gearbox may have an gearbox input shaft. The gearbox input shaft may be rotationally coupled to a spool of the turbine engine. The first starter may have a first-starter shaft. The second starter may have a second-starter shaft. The second-starter shaft may be coaxial with the first-starter shaft. The first starter and the second starter may each be coupled to the gearbox input shaft independently of one another. 1. A system for starting a turbine engine , comprising:a gearbox having a gearbox input shaft; the gearbox input shaft rotationally coupled to a spool of the turbine;a first starter having a first-starter shaft; anda second starter having a second-starter shaft, said second-starter shaft being coaxial with the first-starter shaft,wherein the first starter and second starter are each coupled to said gearbox input shaft independently of one another.2. The system of claim 1 , wherein the first starter is an electric starter and said second starter is an air turbine starter.3. The system of claim 1 , wherein the first starter separates the gearbox and the second starter.4. The system of claim 1 , wherein the second-starter shaft is located radially inward of the first-starter shaft.5. The system of claim 1 , wherein the second starter is selectively coupleable to said gearbox input shaft.6. The system of claim 1 , further comprising a second gearbox coupling said gearbox input shaft and one of said first and second starters.7. The system of claim 1 , wherein both of said first and second starters are selectively coupleable to said gearbox input shaft.8. The system of claim 1 , further comprising a mounting member connected to one of said first and second starters and to a casing of said turbine engine.9. The system of claim 8 , wherein said mounting member comprises an damping member.10. A system for starting a turbine engine claim 8 ...

COMBINED CYCLE PLANT, DEVICE FOR CONTROLLING SAID PLANT, AND METHOD FOR STARTING UP SAID PLANT

A combined cycle plant, a device for controlling a combined cycle plant, and a method for starting up a combined cycle plant, wherein the time for starting up the combined cycle plant can be shortened by providing: a gas turbine having a compressor, a combustor, and a turbine; a heat recovery steam generator for generating steam by means of the exhaust heat of exhaust gas from the gas turbine; a steam turbine driven by means of the steam generated by the heat recovery steam generator; and a control device configured to set a standby load for the gas turbine during a start-up continuously to change in accordance with a change in metal temperature of the steam turbine. 116-. (cancelled)17. A combined cycle plant comprising:a gas turbine that has a compressor, a combustor, and a turbine;a heat recovery steam generator that generates steam by means of exhaust heat of exhaust gas from the gas turbine;a steam turbine that is driven by means of steam generated by the heat recovery steam generator; anda control device configured to set a standby load which is a load retained on the gas turbine when the gas turbine is started up to change continuously in accordance with a change in metal temperature of the steam turbine.18. The combined cycle plant according to claim 17 ,wherein the standby load is a function of the metal temperature and increases in accordance with a rise of the metal temperature.19. The combined cycle plant according to claim 18 ,wherein the standby load is a function including a low temperature region and a high temperature region with respect to the metal temperature, and a changing rate of the standby load with respect to the metal temperature in the low temperature region and that in the high temperature region are varied from each other.20. The combined cycle plant according to claim 19 ,wherein the changing rate of the standby load in the high temperature region is set to be greater than the changing rate of the standby load in the low temperature ...

COMBINED CYCLE PLANT, CONTROL DEVICE THEREOF, AND STEAM TURBINE STARTUP METHOD

To provide a combined cycle plant, a control device thereof, and a steam turbine startup method that are aimed at improving the operability of a combined cycle plant by allowing a quick change of the output. A combined cycle plant is provided with: a gas turbine having a compressor, a combustor, and a turbine; a supplementary firing burner that raises the temperature of exhaust gas of the gas turbine; a heat recovery steam generator that generates steam using exhaust heat of the exhaust gas; a steam turbine that is driven by steam generated by the heat recovery steam generator; and a control device that changes both an output of the combustor and an output of the supplementary firing burner when an output of the combined cycle plant is to be changed. 1. A method of starting up a combined cycle plant , the combined cycle plant comprising:a gas turbine having a compressor, a combustor, and a turbine;a supplementary firing burner that raises a temperature of exhaust gas of the gas turbine;a heat recovery steam generator that generates steam using exhaust heat of the exhaust gas; anda steam turbine that is driven by steam generated by the heat recovery steam generator,the method comprising:changing both an output of the combustor and an output of the supplementary firing burner when an output of the combined cycle plant is to be changed; andselecting a first output change mode at startup of the steam turbine, and switching to a second output change mode after completion of warming up of the steam turbine,wherein in the first output change mode, the output of the combustor is changed and the output of the supplementary firing burner is held constant when the output of the combined cycle plant is to be changed,in the second output change mode, both the output of the combustor and the output of the supplementary firing burner are changed when the output of the combined cycle plant is to be changed, andthe first output change mode and the second output change mode are ...

METHOD AND SYSTEM FOR SAFE GAS TURBINE STARTUP

A method for safe gas turbine startup is disclosed. The method comprises a first step wherein a fuel metering valve () arranged along a fuel delivery line is tested for possible leakages. If the leakage test is successfully passed, a subsequent turbine startup step can be performed. Further disclosed is a gas turbine engine () comprising a fuel supply system () comprised of a fuel delivery line () and a valve arrangement () positioned along said fuel delivery line (). The valve arrangement () further comprises sequentially arranged shut off valves () and a fuel metering valve (), positioned downstream of the shut off valves (). A pressure measuring arrangement () is further provided, adapted to measure fuel pressure in at least one portion of the fuel delivery line () upstream of the fuel metering valve (). 1. A method for safe gas turbine startup , comprising the following steps:{'b': 33', '21', '7', '3, 'performing a leakage test of a fuel metering valve () positioned along a fuel delivery line () and fluidly coupled with a combustor section () of the gas turbine engine (),'}when the leakage test is successfully passed, initiating a gas turbine engine startup procedure.233. The method of claim 1 , wherein the step of performing the leakage test of the fuel metering valve () further comprises the following steps:{'b': 33', '33, 'establishing a first test pressure in a closed volume upstream of the fuel metering valve (), while the fuel metering valve () is closed; wherein said first test pressure is preferably lower than a full fuel supply pressure;'}{'b': '33', 'detecting a pressure drop upstream of the fuel metering valve ();'}if the pressure drop is above a threshold value, generating a leakage alert signal;if the pressure drop is below the threshold value, executing a further step of the startup procedure.3. The method of claim 2 , wherein the step of establishing the first test pressure comprises the steps of:{'b': '33', 'establishing a full fuel supply ...

DECOUPLER ASSEMBLIES FOR ENGINE STARTER

An air turbine starter for starting an engine, comprising a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through. A turbine member is journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas. A gear train is drivingly coupled with the turbine member, a drive shaft is operably coupled with the gear train, and an output shaft is selectively operably coupled to rotate with the engine via a decoupler. 1. An air turbine starter for starting an engine , comprising:a housing defining an inlet, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of gas there through;a turbine member journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas;a gear train drivingly coupled with the turbine member;a drive shaft operably coupled with the gear train and having ramped teeth on its output end; and an output shaft having a first end with mating ramped teeth that are selectively operably coupled to the drive shaft and a second end configured to be operably coupled to and rotate with the engine, the ramped teeth allow for driving torque transfer from the drive shaft to the output shaft and the ramped teeth slide on each other when back driving torque is transmitted such that the output shaft is moved away from the drive shaft;', 'a connector having a body with a first and second end and extending between the output shaft and the drive shaft; and', 'a magnetic coupling selectively linking the drive shaft to the output shaft via the connector, when driving torque is transmitted the connector is magnetically linked to one of the output shaft or the drive shaft via the magnetic coupling and when back driving torque is transmitted the connector is moved away from at least a portion of the magnetic coupling., 'a decoupler, ...

SYSTEM AND METHOD FOR OPERATING A POWER PLANT

A system including a fuel-supply system including, an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system, an expander configured to generate power by expanding an oxidant from the gas-turbine system, and a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator 1. A system , comprising: an auxiliary-fuel-gas compressor configured to compress a fuel for use by a gas-turbine system;', 'an expander configured to generate power by expanding an oxidant from the gas-turbine system; and', 'a motor/generator configured to function in a motor mode and in a generator mode, wherein the motor/generator drives fuel compression with the auxiliary fuel-gas compressor in the motor mode, and the motor/generator generates power in the generator mode as the expander uses oxidant from the gas-turbine system to drive the motor/generator., 'a fuel-supply system comprising2. The system of claim 1 , comprising a fuel-gas compressor/expander having both the auxiliary-fuel gas compressor and the expander as a single dual-purpose unit.3. The system of claim 1 , comprising a controller configured to change the motor/generator between the motor mode and the generator mode.4. The system of claim 3 , comprising a clutch configured to engage and disengage the auxiliary-fuel-gas compressor from the motor/generator claim 3 , wherein the controller controls operation of the auxiliary-fuel-gas compressor by engaging and disengaging the clutch.5. The system of claim 3 , wherein the controller controls the release of oxidant from the gas-turbine system to the expander.6. The system of claim 3 , comprising a primary-fuel-gas compressor.7. The system of claim 6 , wherein the controller ...

SYSTEM, PROPULSION SYSTEM AND VEHICLE

One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. 120-. (canceled)21. A propulsion system for an aircraft , comprising:a gas turbine engine including a spool configured to power a propulsor;an auxiliary power unit (APU) configured to be engaged with the spool to supply power to the propulsor sufficient to taxi the aircraft;a controller configured to selectively engage the APU to the spool to taxi the aircraft without starting the gas turbine engine.22. The propulsion system of claim 21 , further comprising a clutch mechanically coupled between the APU and the spool claim 21 , wherein the clutch is configured to mechanically engage and disengage the APU respectively to and from the spool.23. The propulsion system of claim 22 , wherein the controller is configured to control the clutch to selectively engage the APU to the spool to power the propulsor to taxi the aircraft without starting the gas turbine engine.24. The propulsion system of claim 21 , wherein the controller is configured to selectively disengage the APU from the spool during one or more of takeoff claim 21 , cruise and landing modes.25. The propulsion system of claim 21 , wherein the controller is configured to selectively engage the APU to the spool during one or more of takeoff claim 21 , cruise and landing modes claim 21 , to provide supplemental power to the spool.26. The propulsion system of claim 21 , wherein the controller is configured to selectively engage the APU to the spool to start or aid in the starting of the gas turbine engine following completion of the taxiing operation.27. The propulsion ...

EQUIPMENT HEALTH MONITORING METHOD AND SYSTEM AND ENGINE

An Equipment Health Monitoring method for an engine and an Equipment Health Monitoring system for performing the method are provided. At least some of the following units are used: an Engine Simulation Unit, a Possibilistic Drift Computation Unit, a Fuzzy String Generator Unit, an Experience-based String Matching Unit and an Information Fusion and Prognosis Unit. 1. An Equipment Health Monitoring method for an engine with the following stepsa) a possibilistic drift computation unit automatically allots an upper probability distribution to drift rates of the differences between measured and predicted values generated by an engine simulation unit,b) a fuzzy string generator unit transforms the numerical sequence of upper probabilities of the drift rates generated by the possibilistic drift computation unit into a sequence of quantified terms in a fuzzy term set,c) an experience-based string matching unit compares the string of terms generated by the fuzzy string generator unit with at least one other sequence or portion of sequence of previously obtained fuzzy terms in order to determine the degree of similarity to each of the database set, andd) an information fusion and prognosis unit determining in dependence of the matching patterns or portions of the patterns resulting from the comparisons carried out in the experience-based string matching unit, providing a rate of engine deterioration indicating the current level of deterioration, the rate of deterioration change and the remaining useful life for a given level of deterioration or requirement or otherwise for engine maintenance or the most likely level of deterioration and the likelihood for the requirement or otherwise of engine maintenance of the engine under test.2. The Equipment Health Monitoring method according to claim 1 , wherein the data a possibilistic drift computation unit is measured with at least one parameter value at one location of the engine during its operation claim 1 , a data processing unit ...

SYSTEM FOR THE EMERGENCY STARTING OF A TUROMACHINE

The invention relates to a system for emergency starting a turbine engine, characterised in that it comprises a flyer for driving the turbine engine, said flyer comprising a drum () rigidly connected to a rotary shaft (), the axes of symmetry (LL) of the drum () and of the shaft being coincident, the flyer further comprising at least one exhaust nozzle () for ejecting gas, which is positioned on the periphery of the drum () and oriented substantially tangentially to the rotation about said axis (LL), and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle (), said emergency start system further comprising a support in which the shaft of the flyer rotates, and a volute for recovering the gases, which radially surrounds the flyer and is rigidly connected to said support. 1. A system for emergency starting a turbine engine , characterised in that it comprises a flyer for driving the turbine engine , said flyer comprising a drum rigidly connected to a rotary shaft , the axes of symmetry of the drum and of the shaft being coincident , the flyer further comprising at least one exhaust nozzle for ejecting gas , which is positioned on the periphery of the drum and oriented substantially tangentially to the rotation about said axis , and a pyrotechnic gas generation device which is installed in the flyer and feeds said at least one exhaust nozzle , said emergency start system further comprising a support in which the shaft of the flyer rotates , and a volute for recovering the gases , which radially surrounds the flyer and is rigidly connected to said support.2. A system according to claim 1 , wherein the gas generation device comprises a solid propellant block.3. A system according to claim 2 , wherein a combustion chamber feeding said at least one exhaust nozzle is formed in the solid propellant block.4. A system according to claim 1 , wherein said at least one exhaust nozzle is a two-dimensional exhaust nozzle.5. ...

COMPRESSOR START BLEED SYSTEM FOR A TURBINE SYSTEM AND METHOD OF CONTROLLING A COMPRESSOR START BLEED SYSTEM

A compressor start bleed system for a turbine system includes a compressor section. Also included is a turbine section disposed downstream of the compressor section. Further included is at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section. Yet further included is at least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system. 1. A compressor start bleed system for a turbine system comprising:a compressor section;a turbine section disposed downstream of the compressor section;at least one duct fluidly coupled to the compressor section, wherein the at least one duct is configured to route a start bleed extraction from the compressor section to a location downstream of the turbine section; andat least one control device of the at least one duct configured to actively modulate the start bleed extraction during a part speed operation of the turbine system.2. The compressor start bleed system of claim 1 , further comprising a control unit comprising a control schedule.3. The compressor start bleed system of claim 2 , wherein the control unit is in operative communication with the at least one control device.4. The compressor start bleed system of claim 2 , wherein the control schedule comprises at least one operating parameter over a compressor part speed operating range.5. The compressor start bleed system of claim 2 , wherein the control schedule comprises a compressor operating limit line.6. The compressor start bleed system of claim 4 , wherein the at least one operating parameter comprises a fuel-air ratio of a combustor section of the turbine system.7. The compressor start bleed system of claim 1 , wherein the control device comprises a variable valve disposed at least partially within the at least one duct. ...

GAS TURBINE COMBINED CYCLE FOR HIGH FLEXIBILITY

A combined cycle power generation plant has parallel normally-independent power generation trains, each having a gas turbine in line with a heat recovery steam generator. In a “parked” or spinning reserve operational state, combustion is discontinued at the gas turbine of one power generation train, placed on turning fear. Combustion at the other power train is reduced, preferably to a minimum emissions-compliant level (NOx, CO) of the gas turbine operated at low level combustion. A bypass duct with controllable dampers apportions exhaust from the operating gas turbine to the heat recovery steam generators of both power trains. This maintains an elevated temperature in both heat recovery steam generators and enables fast restart. 1. A combined cycle power plant , comprising:at least two gas turbines operable to combust fuel during operation and supplying torque to at least one electrical generator via a shaft, each of the gas turbines producing an exhaust flow during operation, the exhaust being coupled in a flow path to at least one of two or more heat recovery steam generators, each of the heat recovery steam generators being associated with a respective one of the gas turbines in a power train, the heat recovery steam generators producing steam from the exhaust of the gas turbines during operation for extraction of further energy by a steam turbine;operational controls configured to assume a low load operational state of the combined cycle power plant wherein an active one of the two or more gas turbines is operated at a predetermined low load level and an other of the two or more gas turbines is substantially shut down;a bypass duct for defining a flow path for gas turbine exhaust from an outlet of one of the gas turbines in one of the power trains to an inlet of the heat recovery steam generators of the other power trains;wherein in the low load operational state, the bypass duct conveys a portion of the exhaust gas produced by the active one of the two or more ...

STARTER AIR VALVE SYSTEMS CONFIGURED FOR LOW SPEED MOTORING

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position. 1. A starter air valve (SAV) system comprising:a pressure actuated SAV actuator configured to be operatively connected to a SAV; anda first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator;a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator; anda manual override (MOR) valve selector disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.2. The system of claim 1 , wherein at least one of the first pressure valve or second pressure valve is a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator.3. The system of claim 1 , wherein the SAV includes at least one of a butterfly valve or an inline valve ...

Starter air valve systems configured for low speed motoring

A starter air valve (SAV) system includes a pressure actuated SAV actuator configured to be operatively connected to a SAV, a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator, and a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator. A manual override (MOR) valve selector is disposed between the first pressure valve, the second pressure valve, and the SAV actuator, the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly connect the second pressure valve and the SAV actuator in a second position.

GUIDE VANE CONNECTION

Disclosed is a lever linkage for the rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine, wherein the guide vane has a vane shaft, which extends along a vertical axis. In accordance with the invention, the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve, which coaxially surrounds the vane shaft in sections, and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection, and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by means of a fastening element, in particular a threaded nut. In consequence thereof, a separation of two different force flows that act on the guide vanes is obtained, as a result of which local load peaks are reduced. 1. A lever connection for rotationally fixed connection of a guide vane to a lever of a guide vane adjusting device of a turbomachine , wherein the guide vane has a vane shaft , which extends along a vertical axis , hereby characterized in that the lever is formed in one piece at a radially outer end of an essentially hollow cylindrical clamping sleeve , which coaxially surrounds the vane shaft in sections , and the vane shaft and the clamping sleeve are coupled by way of a longitudinal side form-fitting connection or a front-end form-fitting connection , and the vane shaft can be tensioned with the clamping sleeve along the vertical axis by a fastening element , in particular a threaded nut.2. The lever linkage according to claim 1 , wherein the clamping sleeve has a collar for the radial positional securing of the guide vane in a housing of the turbomachine claim 1 , wherein claim 1 , between the collar and the housing claim 1 , there is a defined gap.3. The lever linkage according to wherein claim 1 , between a radially inner end of the clamping sleeve and the collar of the clamping sleeve claim 1 , a ...

Methods and apparatus for controlling at least part of a start-up or re-light process of a gas turbine engine

A method of controlling at least part of a start-up or re-light process of a gas turbine engine, the method comprising: determining when a flame in a combustion chamber of a gas turbine engine is extinguished, during a start-up process or re-light process or during operation; purging the combustion chamber by controlling rotation of a low pressure compressor using a first electrical machine, and controlling rotation of a high pressure compressor using a second electrical machine, the combustion chamber downstream of the low pressure compressor and high pressure compressor; and controlling rotation of the low pressure compressor using the first electrical machine, and controlling rotation of the high pressure compressor using the second electrical machine to restart the start-up process or perform the re-light process.

Plant state monitoring method, plant state monitoring computer program, and plant state monitoring apparatus

Provided is a plant state monitoring method which monitors an operation state of a plant by using the Mahalanobis distance based on the plant state amount. The method creates a first unit space as a set of data used to be a reference when judging whether the plant operation state during a start operation period is normal according to the state amount in the plant start operation period. The method also creates a second unit space as a set of data used to be a reference when judging whether the plant operation state during a load operation period is normal according to the state amount in the plant load operation period.

Rotor bow management

A method of reducing rotor bow in a high pressure rotor of a gas turbine engine that has in axial flow a low pressure rotor and a high pressure rotor. The method involves storing bleed air from the gas turbine engine when the engine is running to provide stored pneumatic energy; and using that stored pneumatic energy after the engine has been shut-down to rotate the high pressure rotor at a speed and for a duration that reduces rotor bow. A gas turbine engine wherein rotor bow in the high pressure rotor after engine shut-down has been reduced by carrying out the aforesaid method is also disclosed.

TURBOCHARGER HAVING THRUST BEARING WITH BIASED OIL FLOW

A turbocharger includes a turbine wheel, a compressor wheel, a shaft coupled to the turbine wheel and the compressor wheel, and a thrust bearing. The thrust bearing includes a loaded side and an unloaded side. The loaded side bears a majority of axial loading caused by force imbalances between the turbine wheel and the compressor wheel during engine startup. The thrust bearing restricts oil flow to the unloaded side as compared to the loaded side during engine startup. 1. A turbocharger comprising:a turbine wheel, a compressor wheel, and a shaft coupled to the turbine wheel and the compressor wheel; anda thrust bearing having a loaded side and an unloaded side, the loaded side bearing a majority of axial loading caused by force imbalances between the turbine wheel and the compressor wheel during engine startup, wherein the thrust bearing restricts oil flow to the unloaded side as compared to the loaded side during engine startup.2. The turbocharger according to claim 1 , wherein the thrust bearing includes an oil inlet claim 1 , one or more loaded side outlets claim 1 , a loaded side circumferential channel configured to distribute oil from the oil inlet to the loaded side outlets claim 1 , one or more unloaded side outlets claim 1 , and an unloaded side circumferential channel configured to distribute oil from the oil inlet to the unloaded side outlets claim 1 , wherein the unloaded side circumferential channel is a flow restricting channel.3. The turbocharger according to claim 2 , wherein the unloaded side circumferential channel is at least one of elongated or smaller in cross-sectional size as compared to the loaded side circumferential channel.4. The turbocharger according to claim 3 , wherein the unloaded side circumferential channel is elongated in a serpentine manner.5. The turbocharger according to claim 3 , wherein the unloaded side circumferential channel is smaller in cross-sectional size as compared to the loaded side circumferential channel.6. The ...

Solar and steam hybrid power generation system

Solar and steam hybrid power generation system including a solar steam generator, an external steam regulator, a turboset, and a power generator. A steam outlet end of the solar steam generator is connected to a steam inlet of the turboset. A steam outlet end of the external steam regulator is connected to the steam inlet of the turboset. A steam outlet of the turboset is connected to the input end of a condenser, and the output end of the condenser is connected to the input end of a deaerator. The output end of the deaerator is connected to the input end of a water feed pump. The output end of the water feed pump is connected to a circulating water input end of the solar steam generator. The output end of the water feed pump is connected to a water-return bypass of the external steam.

PNEUMATIC DEVICE FOR RAPIDLY REACTIVATING A TURBINE ENGINE, ARCHITECTURE FOR A PROPULSION SYSTEM OF A MULTI-ENGINE HELICOPTER PROVIDED WITH SUCH A DEVICE, AND CORRESPONDING HELICOPTER

The invention relates to a device for the rapid reactivation of a helicopter turbine engine (), characterised in that it comprises a pneumatic turbine () mechanically connected to said turbine engine () so as to be able to rotate it and ensure reactivation thereof; a pneumatic storage () connected to said pneumatic turbine () by means of a pneumatic circuit () for supplying pressurised gas to said pneumatic turbine (); a controlled fast-opening pneumatic valve () arranged on the pneumatic circuit () between said storage () and said pneumatic turbine () and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine (), or in a closed position in which said pneumatic turbine () is no longer supplied with pressurised gas. 1. A device for the rapid reactivation of a helicopter turbine engine , wherein it comprises:a pneumatic turbine mechanically connected to said turbine engine so as to be able to rotate it and ensure reactivation thereof;a pneumatic storage connected to said pneumatic turbine by means of a pneumatic circuit for supplying pressurised gas to said pneumatic turbine,a controlled fast-opening pneumatic valve arranged on the pneumatic circuit between said storage and said pneumatic turbine and suitable for being on demand placed at least in an open position in which the gas can supply said pneumatic turbine, thus allowing reactivation of said turbine engine, or in a closed position in which said pneumatic turbine is no longer supplied with pressurised gas.2. The device according to claim 1 , wherein it further comprises a pressure reducer arranged on said pneumatic circuit between said pneumatic valve and said pneumatic turbine and configured to regulate the pressure of said gas supplying said pneumatic turbine.3. The device according to claim 1 , wherein said pneumatic turbine is mechanically connected to said turbine engine by means of at least one free-wheel.4. The device according to claim 1 , ...

STARTER CONTROLLER

Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to a method for starting an engine using an integrated starter. The integrated starter includes a starter air valve and an air turbine starter. The method includes receiving one or more signals indicative of one or more parameters. The method includes determining a valve setting for the starter air valve based at least in part on the one or more signals indicative the one or more parameters. The method includes providing one or more control signals to adjust a position of the starter air valve based at least in part on the valve setting. The position of the starter air valve regulates the flow of fluid into the air turbine starter. 1. A method for starting an engine using an integrated starter , the integrated starter comprising a starter air valve and an air turbine starter , the method comprising:receiving one or more signals indicative of one or more parameters;determining a valve setting for the starter air valve based at least in part on the one or more signals indicative of the one or more parameters; andproviding one or more control signals to adjust a position of the starter air valve based at least in part on the valve setting,wherein the position of the starter air valve regulates the flow of fluid into the air turbine starter.2. The method of claim 1 , wherein the valve setting is an initial setting for the starter air valve.3. The method of claim 2 , further comprising:receiving one or more environmental parameters;determining a second valve setting based on the one or more environmental parameters; andproviding one or more second control signals to adjust the position of the starter air valve based at least in part on the second valve setting.4. The method of claim 3 , wherein the one or more environmental parameters comprise a pressure.5. The method of claim 3 , wherein the one or more environmental parameters comprise a ...

FAN ARRANGEMENT FOR A GAS TURBINE ENGINE

A gas turbine engine for an aircraft including: engine core including a turbine; and fan including a plurality of fan blades extending radially from a hub, each fan blade having a leading and trailing edge. Turbine includes a lowest pressure turbine stage having a row of rotor blades each extending radially and having a leading and trailing edge. A fan-turbine radius difference is measured as radial distance between: a point on a circle swept by a radially outer tip of the trailing edge of each of the rotor blades of the lowest pressure stage of the turbine; and a point on a circle swept by a radially outer tip of the leading edge of each of fan blades; and a fan speed to fan-turbine radius ratio defined as: 2. The gas turbine engine of claim 1 , wherein the fan speed to fan-turbine radius ratio is in a range between 1.5 rpm/mm and 4.0 rpm/mm.3. The gas turbine engine of claim 1 , wherein the fan speed to fan-turbine radius ratio is in a range between 1.5 rpm/mm and 3.6 rpm/mm.4. (canceled)5. The gas turbine engine of claim 1 , wherein the fan-turbine radius difference is in a range between 50 cm and 120 cm.6. The gas turbine engine of claim 1 , wherein the fan-turbine radius difference is in a range between 55 cm to 85 cm claim 1 , and the fan tip radius of the gas turbine engine is in the range from 110 cm to 150 cm.7. (canceled)8. The gas turbine engine of claim 1 , wherein the maximum take-off rotational fan speed is in a range between 1450 rpm and 3020 rpm.9. The gas turbine engine of claim 1 , wherein the maximum take-off rotational fan speed is in a range between 2100 rpm and 3020 rpm claim 1 , and the fan tip radius of the gas turbine engine is in the range from 110 cm to 150 cm.10. (canceled)1149. The gas turbine engine of claim 1 , wherein a rotor of the lowest pressure turbine stage is shrouded claim 1 , and the radially outer tip of the trailing edge of each of the rotor blades is measured to the underside of the shroud ().12. The gas turbine engine of ...

Method for starting up a gas and steam turbine system

A method for starting a gas and steam turbine system which includes a gas turbine system which includes at least one gas turbine, in addition to at least one steam turbine system which includes at least one steam turbine and at least one steam system is provided. Heat produced by the working fluid and which is released in the gas turbine is guided to the steam system in order to produce steam which drives the steam turbine. During starting, the gas turbine is started prior to the steam turbine and the steam turbine is started in the presence of the first steam in the system and is impinged upon by said steam.

Method for operating a combined cycle power plant

A method for operating a combined cycle power plant is disclosed, which has a gas turbine installation and a water-steam cycle connected to the gas turbine installation by a waste heat steam generator and has at least one steam turbine, the gas turbine installation includes a compressor, a combustion chamber, and a turbine. To cool the turbine, air compressed at the compressor is removed, cooled in at least one cooler flowed through by water, thus generating steam, and introduced into the turbine. At least with the gas turbine installation running, prior to or during the start-up of the water-steam cycle, waste heat, which is contained in the steam generated in the at least one cooler, is used to good effect for pre-heating the installation inside the combined cycle power plant.

PRE-START MOTORING SYNCHRONIZATION FOR MULTIPLE ENGINES

An aspect includes a system for pre-start motoring control for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to control a motoring time of the first engine starting system relative to one or more other engine starting systems of one or more other engines of the aircraft by adjusting the motoring time of the first engine starting system within a tolerance of the motoring time of the one or more other engine starting systems in a pre-start motoring sequence. 1. A system for pre-start motoring control for multiple engines of an aircraft , the system comprising:a first engine starting system of a first engine; anda controller operable to control a motoring time of the first engine starting system relative to one or more other engine starting systems of one or more other engines of the aircraft by adjusting the motoring time of the first engine starting system within a tolerance of the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.2. The system as in claim 1 , wherein the motoring time of the first engine starting system is controlled relative to the one or more other engine starting systems by comparing a first value of the motoring time of the first engine starting system with a first value of the motoring time of the one or more other engine starting systems and selecting a relative value as the motoring time for the first engine starting system and the one or more other engine starting systems.3. The system as in claim 2 , wherein the controller provides the first value of the motoring time of the first engine starting system to one or more other controllers and receives the first value of the motoring time of the one or more other engine starting systems from the one or more other controllers.4. The system as in claim 2 , wherein the controller maintains the motoring time of the first engine starting system as the ...

Steam turbine plant and cooling method for same

A steam turbine plant is provided with: a boiler; a fuel valve; a low-temperature steam generation source; a steam turbine; a main steam line that guides steam generated in the boiler to the steam turbine; a main steam adjustment valve that is provided to the main steam line; a low-temperature steam line that guides low-temperature steam from the low-temperature generation source to a position closer to the steam turbine-side than the main steam adjustment valve in the main steam line; a low-temperature steam valve provided to the low-temperature steam line; and a control device. During a stopping process of the steam turbine plant, the control device sends a command to close the fuel valve, and then sends a command to open the low-temperature steam valve.

TURBOMACHINE ACCESSORY GEARBOX BRACKET

A gearbox assembly includes a housing structure, a shear bracket that connects the housing structure to a hanger to hold the housing structure relative to a turbomachine, and a thermal spray layer between the shear bracket and the housing structure. 1. A gearbox assembly , comprisinga housing structure;a shear bracket that connects the housing structure to a hanger to hold the housing structure relative to a turbomachine; anda thermal spray layer between the shear bracket and the housing structure.2. The gearbox assembly of claim 1 , wherein a portion of the shear bracket is coated in the thermal spray layer.3. The gearbox assembly of claim 2 , wherein the shear bracket interfaces with the housing structure through the portion.4. The gearbox assembly of claim 1 , wherein the housing structure and the shear bracket interface with each other through the thermal spray layer.5. The gearbox assembly of claim 1 , wherein the thermal spray layer is planar and lacks serrations.6. The gearbox assembly of claim 1 , including a plurality of mechanical fasteners that secure the shear bracket to the housing structure.7. The gearbox assembly of claim 1 , wherein the thermal spray comprises nickel and aluminum composite particles.8. The gearbox assembly of claim 1 , wherein the turbomachine is a land-based turbomachine.9. The gearbox assembly of claim 1 , including a gear train housed within the housing structure and a starter secured to the housing structure.10. The gearbox assembly of claim 6 , wherein the starter is a hydraulic starter.11. The gearbox assembly of claim 1 , wherein the thermal spray layer is a plasma spray layer.12. A turbomachine assembly claim 1 , comprising:a turbomachine engine;a housing structure;a gear train within the housing structure that is selectively driven by the turbomachine;a starter within the housing structure that selectively drives the turbomachine; anda shear bracket connecting a flange of the housing structure to a hanger of the turbomachine ...

TURBOMACHINE WITH AN ELECTRIC MACHINE ASSEMBLY AND METHOD FOR OPERATION

A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component. 1. A method for operating a turbomachine , the method comprising:rotating a first rotatable component at a first speed, wherein the first rotatable component comprises a first compressor, and wherein the first rotatable component is operably coupled to a first electric machine;rotating a second rotatable component at a second speed, wherein the second rotatable component comprises a second compressor, and wherein the second rotatable component is operably coupled to a second electric machine; andtransferring energy generated from at least one of the first electric machine or the second electric machine to adjust the first speed or the second speed based on a compressor map determinative of a desired operating condition relative to one or more of a stall margin, a surge margin, an operating pressure ratio, or an operating speed.2. The method of claim 1 , wherein ...

STARTER AIR VALVE SYSTEM WITH DUAL ELECTROMECHANICAL CONTROLS

According to an aspect, a system includes a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source. The system also includes a variable-position electromechanical device operable to adjust positioning of the starter air valve and a discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device. 1. A system comprising:a starter air valve in fluid communication with an air turbine starter to drive motoring of a gas turbine engine responsive to a compressed air flow from a compressed air source;a variable-position electromechanical device operable to adjust positioning of the starter air valve; anda discrete-position electromechanical device operable to adjust positioning of the starter air valve and limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to a pulse width modulation control based on a failure of the variable-position electromechanical device.2. The system as in claim 1 , wherein the compressed air source is an auxiliary power unit claim 1 , a ground cart claim 1 , or a cross-engine bleed.3. The system as in claim 1 , further comprising a pneumatic actuator operable to drive rotation of a valve plate of the starter air valve to establish a valve-controlled starter air flow to the air turbine starter based on the compressed air flow.4. The system as in claim 3 , wherein the variable-position electromechanical device and the discrete-position electromechanical device are pneumatically coupled to the pneumatic actuator.5. The system as in claim 4 , wherein the variable-position electromechanical device is positioned in a pneumatic ...

AIRFLOW CONTROL FOR AIR TURBINE STARTER

An example arrangement for cooling a gas turbine engine includes an air turbine starter having a turbine section for rotationally driving a compressor through rotation of a shaft. An starter air valve is configured to control a flow of pressurized air that flows downstream towards turbine blades of the air turbine starter. An airflow adjustment device (AAD) is configured to adjust the flow when a manual override feature of the starter air valve is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor. A governor is configured to control a degree to which the AAD adjusts the flow. The governor is mechanically linked to the shaft through one or more gears and configured to adjust the AAD such that a rotational speed of said one the shafts does not exceed a predefined threshold during a particular operating mode. 1. An arrangement for cooling a gas turbine engine comprising:an air turbine starter comprising a turbine section for rotationally driving a compressor of a gas turbine engine through rotation of a shaft that connects the turbine section to the compressor;a starter air valve configured to control a flow of pressurized air along a flow path that flows downstream towards turbine blades of the turbine section, the starter air valve having a manual override feature that allows manual opening of the starter air valve;an airflow adjustment device configured to adjust the flow of pressurized air along the flow path when the manual override feature is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor; anda governor configured to control a degree to which the airflow adjustment device adjusts the flow, the governor mechanically linked to the shaft through one or more gears and configured to adjust the airflow adjustment device such that a rotational speed of said one of the shafts does not exceed a predefined threshold during a particular operating ...

GAS TURBINE HAVING AN ANNULAR PASSAGE SUBDIVIDED INTO ANNULUS SECTORS

A gas turbine having at least one inner and outer housing part, between which two housing parts a ring channel is at least partially arranged, which ring channel circumferentially surrounds the useful flow of the working fluid prevailing during operation of the gas turbine and circumferentially surrounds the gas turbine rotor. The ring channel is designed to conduct a cooling fluid in the circumferential direction, wherein the ring channel is divided into ring sectors in the circumferential direction by separators. A tube is at least partially provided in the ring channel which fluidically connects individual ring sectors to each other, and is designed as a distributing tube, which is fluidically connected to at least one cooling-fluid line for conducting cooling fluid and has at least one outlet opening, which at least one outlet opening is designed to transfer the cooling fluid from the tube into the ring sectors. 110.-. (canceled)11. A gas turbine comprising:at least one inner casing part and at least one outer casing part, between which both casing parts is at least partially arranged an annular passage which circumferentially encloses the useful flow of the working fluid, which prevails during operation of the gas turbine, and the gas turbine rotor, wherein the annular passage is designed to direct a cooling fluid in the circumferential direction,wherein the annular passage is fluidically subdivided into annulus sectors in the circumferential direction by partitions, designed as separating plates, which are adapted to prevent a free, unhindered fluid exchange between the individual annulus sectors,wherein provision is made at least partially in the annular passage for a pipe which fluidically interconnects individual annulus sectors, wherein the pipe is designed as a distribution pipe which is fluidically connected to at least one cooling fluid feed line for cooling fluid feed and has at least one outlet opening, which is designed for the transfer of cooling ...

Bowed rotor start response damping system

A method of bowed rotor start response damping for a gas turbine engine is provided. A spring rate and a damping characteristic of one or more bearing supports in the gas turbine engine are selectively modified while a shaft of the gas turbine engine rotates below a speed which is adversely affected by a bowed rotor condition of the gas turbine engine.

AIRFLOW CONTROL FOR AIR TURBINE STARTER

An example arrangement for cooling a gas turbine engine includes an air turbine starter, a starter air valve, and an airflow adjustment device. The air turbine starter includes a turbine section for rotationally driving a compressor of a gas turbine engine through rotation of a shaft that connects the turbine section to the compressor. The starter air valve is configured to control a flow of pressurized air along a flow path from a source to turbine blades of the turbine section. The starter air valve includes a manual override feature that allows manual opening of the starter air valve. The airflow adjustment device is configured to adjust the flow of pressurized air along the flow path when the manual override feature is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor. 1. An arrangement for cooling a gas turbine engine comprising:an air turbine starter comprising a turbine section for rotationally driving a compressor of a gas turbine engine through rotation of a shaft that connects the turbine section to the compressor;a starter air valve configured to control a flow of pressurized air along a flow path from a source to turbine blades of the turbine section, the starter air valve having a manual override feature that allows manual opening of the starter air valve; andan airflow adjustment device configured to adjust the flow of pressurized air along the flow path when the manual override feature is engaged based on a rotational speed of one of the shaft and an additional shaft that is driven by the compressor.2. The arrangement of claim 1 , further comprising a control device configured to control a degree to which the air flow adjustment device adjusts the flow.3. The arrangement of claim 2 , further comprising:a speed sensor configured to measure a rotational speed of said one of the shafts;wherein the control device comprises an electrical controller in communication with the speed sensor and ...

SYSTEM AND METHOD FOR CONTROLLING AN AUXILIARY POWER UNIT INLET DOOR

A system and method for controlling an inlet door of an auxiliary power unit (APU) are provided. It is determined whether a condition to inhibit a start of the APU is present. If no condition to inhibit the start of the APU is present, a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the APU is output. If the condition to inhibit the start of the APU is present, a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position is output. 1. A method for controlling an inlet door of an auxiliary power unit , the method comprising:determining whether a condition to inhibit a start of the auxiliary power unit is present;if no condition to inhibit the start of the auxiliary power unit is present, outputting a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the auxiliary power unit; andif the condition to inhibit the start of the auxiliary power unit is present, outputting a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position.2. The method of claim 1 , further comprising receiving input data comprising at least one of a current operating state of the auxiliary power unit claim 1 , an indication as to whether an emergency shutdown of the auxiliary power unit has been commanded claim 1 , and an indication as to whether at least one operational fault causing a shutdown of the auxiliary power unit is present claim 1 , and determining from the input data whether the condition to inhibit the start of the auxiliary power unit is present.3. The method of claim 2 , further comprising determining that no emergency shutdown has been commanded and that no operational fault is present claim 2 , thereby determining that no condition to inhibit the start of the auxiliary power unit is present.4 ...

Water/steam cycle and method for operating the same

A water/steam cycle includes a steam generator, a steam turbine, a water cooled condenser and a feedwater pump. The condenser includes within a condenser shell at least one tube bundle with an internal air cooler, which is connected to an external ejector/vacuum pump by means of a suction line. In order to reduce the condenser evacuation time at the start-up of the water/steam cycle without using auxiliary steam, an additional evacuation line with a motorized isolating valve connects the external ejector/vacuum pump with the condenser shell. The action of the isolating valve is controlled by means of a control.

METHOD FOR MANAGING A BREAKDOWN OF A TURBINE ENGINE STARTER VALVE

The present invention concerns a method () for managing a breakdown of a starter valve of a starting circuit of an aircraft turbine engine, comprising the following steps: —starting () the turbine engine, a state-change command being sent to the starter valve in order for it to open;—increasing () the engine speed of the turbine engine to a predefined first threshold,—during said increase () in engine speed,—if a difference in position has been detected () between the position sensors before the step of starting the turbine engine or if a difference in position is detected () between said position sensors, determining () the position sensor that has switched between the closed position and the open position, the other position sensor having remained in the open or closed position;—when the first threshold is reached, storing () the position sensor that has switched between the closed position and the open position as healthy and the position sensor that has remained in the open or closed position as faulty, so as to measure the state of the starter valve only on the basis of the position of the healthy position sensor. 2. The method according to claim 1 , wherein it is verified claim 1 , during the initiation of the starting of the turbine engine or when the turbine engine has reached the first threshold claim 1 , that a difference is still detected between the positions of the position sensors.3. The method according to claim 1 , wherein the engine speed corresponds to the speed of rotation of a high-pressure shaft of the turbine engine.4. The method according claim 1 , wherein when the turbine engine reaches the first threshold claim 1 , a combustion chamber of the turbine engine is not yet lit.5. The method according to claim 1 , further comprising the steps of:lighting a combustion chamber of the turbine engine;increasing the engine speed of the turbine engine until a second predetermined threshold; sending a state change command to the starter air valve so that ...

STARTER AIR VALVE SYSTEMS CONFIGURED FOR LOW SPEED MOTORING

A starter air valve (SAV) system can include a pressure actuated SAV actuator configured to be operatively connected to a SAV and a first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator. The first pressure valve can be a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator. 1. A starter air valve (SAV) system comprising:a pressure actuated SAV actuator configured to be operatively connected to a SAV; anda first pressure valve configured to selectively allow pressure from a pressure source to the SAV actuator when in fluid communication with the SAV actuator;wherein the first pressure valve is a pulse-width modulation solenoid valve configured to provide a duty cycle of pressure from the pressure source to the SAV actuator.2. The system of claim 1 , wherein the SAV includes at least one of a butterfly valve or an inline valve.3. The system of claim 1 , further comprising a first controller in operable communication with at least the first pressure valve and configured to control the first pressure valve.4. The system of claim 3 , wherein the first controller is an engine computer.5. The system of claim 3 , further comprising a second pressure valve configured to selectively allow pressure from the pressure source to the SAV actuator when in fluid communication with the SAV actuator.6. The system of claim 5 , further comprising a second controller in operable communication with at least the second pressure valve and configured to control the second pressure valve.7. The system of claim 6 , a manual override (MOR) valve selector disposed between the first pressure valve claim 6 , the second pressure valve claim 6 , and the SAV actuator claim 6 , the MOR valve selector configured to selectively fluidly connect the first pressure valve and the SAV actuator in a first position and to fluidly ...

Turbomachine with an electric machine assembly and method for operation

A turbomachine and method for operating a turbomachine comprising a first rotatable component and a second rotatable component each defining a rotatable speed mechanically independent of one another, and an electric machine electrically coupled to the first rotatable component and the second rotatable component such that a load level relative to the first rotatable component and the second rotatable component is adjustable is generally provided. The method includes adjusting a first load at a first rotor assembly of the electric machine electrically coupled to the first rotatable component such that a first speed of the first rotatable component is increased or decreased based on an engine condition and the first load; adjusting a second load at a second rotor assembly of the electric machine electrically coupled to the second rotatable component such that a second speed of the second rotatable component is decreased or increased based on the engine condition and the second load; and transferring electrical energy generated from at least one of the first rotatable component or the second rotatable component.

Methods and apparatus for closed-loop control of a gas turbine

Methods, apparatus, systems and articles of manufacture are disclosed for closed loop control of a gas turbine. An example apparatus includes a frequency band splitter to separate a combustion pulsation signal into a plurality of frequency bands. The example apparatus includes a plurality of subcontrollers, each subcontroller corresponding to one of the frequency bands. Each subcontroller is to be activated at an amplitude threshold associated with the normal operating set point of the frequency band and to generate a correction value while the corresponding frequency band is operating beyond the amplitude threshold. The example apparatus includes a net correction output calculator to aggregate the correction values to generate an aggregated correction value. The example apparatus includes a subcontroller limiter having a maximum limit and/or a minimum limit to inhibit subcontroller(s) from increasing their respective correction values when aggregated correction value is to exceed the maximum limit and/or minimum limit.

METHODS AND SYSTEMS FOR CONTROLLING TURBINE POWERED SYSTEM TO REDUCE STARTUP TIME

A method for operating a power plant may include, during shutdown of a turbine, controlling a damper to move from a first position directing turbine exhaust to enter a heat recovery system to a second position to allow the turbine exhaust to enter a bypass stack and block the turbine exhaust to the heat recovery system. While the position of the damper is maintained in the second position, fired shutdown of the turbine may be performed. In response to instructions to start the turbine, air flow in an exhaust duct for a predetermined period of time is generated, and after generating the air flow for the predetermined period of time, the turbine may be started without performing a purge sequence for the heat recovery system. After starting the turbine, the damper may be controlled between the second position and the first position. 1. A method for operating a power plant including a turbine , a heat recovery system , a bypass stack and an exhaust duct including a damper configured to direct the flow of exhaust from the turbine to the heat recovery system and/or to the bypass stack , the method comprising:before flame out during fired shutdown of the turbine, control the damper to move from a first position directing turbine exhaust to enter the heat recovery system to a second position to allow the turbine exhaust to enter the bypass stack and block the turbine exhaust to the heat recovery system; perform fired shutdown of the turbine;', 'in response to instructions to start the turbine, generate air flow in the exhaust duct for a predetermined period of time; and', 'after generating the air flow for the predetermined period of time, start the turbine without performing a purge sequence for the heat recovery system; and, 'while the position of the damper is maintained in the second position to prevent gas and/or vapor to enter the heat recovery systemafter starting the turbine, control the damper to move from the second position to the first position to allow the ...

METHODS AND APPARATUS FOR CONTROLLING AT LEAST A PART OF A START-UP OR RE-LIGHT PROCESS OF A GAS TURBINE ENGINE

A method of controlling at least a part of a start-up or re-light process of a gas turbine engine, the method comprising: controlling rotation of a low pressure compressor using a first electrical machine to increase angular velocity of the low pressure compressor; and controlling rotation of a high pressure compressor using a second electrical machine to restrict angular velocity of the high pressure compressor while the angular velocity of the low pressure compressor is increased. 1. A method of controlling at least a part of a start-up or re-light process of a gas turbine engine , the method comprising:controlling rotation of a low pressure compressor using a first electrical machine to increase angular velocity of the low pressure compressor; andcontrolling rotation of a high pressure compressor using a second electrical machine to restrict angular velocity of the high pressure compressor while the angular velocity of the low pressure compressor is increased.2. A method as claimed in claim 1 , further comprising: controlling opening of a plurality of variable vanes of the high pressure compressor.3. A method as claimed in claim 1 , further comprising: controlling closing of one of more bleed ports of the high pressure compressor.4. A method as claimed in claim 1 , further comprising: determining if an exit pressure of the low pressure compressor is equal to or greater than a threshold exit pressure; and controlling rotation of the high pressure compressor using the second electrical machine to increase angular velocity of the high pressure compressor if the exit pressure is equal to or greater than the threshold exit pressure.5. A method as claimed in claim 1 , further comprising: controlling ignition within a combustion chamber of the gas turbine engine.6. A method as claimed in claim 5 , further comprising: controlling the first electrical machine and the second electrical machine to function as electrical generators claim 5 , subsequent to controlling ...

Electric unit for a pump-storage power plant

A pumped-storage power plant is disclosed, such as an electric unit having a converter and a rotating electric synchronous machine. The converter is designed as a modular multilevel converter and the machine is directly connectable to the converter, wherein the converter has an adjustable voltage.

GEARED GAS TURBINE ENGINE

A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions. 2. The method of claim 1 , wherein the jet velocity ratio claim 1 , R claim 1 , is between around 0.8 and 1.0 at maximum take-off conditions.3. The method of claim 1 , wherein the jet velocity ratio claim 1 , R claim 1 , is between around 2 and 3 at idle conditions.4. The method of claim 1 , wherein the jet velocity ratio claim 1 , R claim 1 , is between around 0.75 and around 1.3 at cruise conditions.5. The method of claim 1 , wherein the specific thrust is between 80 Nkgs and 90 Nkgs at cruise conditions.6. The method of claim 1 , wherein the fan diameter is between 220 cm and 300 cm.7. The method of claim 6 , wherein the rotational speed of the fan at cruise conditions is in the range of from 1700 rpm to 2500 rpm.8. The method of claim 1 , wherein the fan diameter is between 220 cm and 280 cm.9. The method of claim 1 , wherein the fan diameter is between 320 cm and 380 cm.10. The method of claim 9 , wherein the rotational speed of the fan at cruise conditions is in the range of from 1200 rpm to 2000 rpm.11. The method of claim 9 , wherein the rotational speed of the fan at cruise conditions is in the range of from 1400 rpm to 1800 rpm.12. The method ...

METHOD AND SYSTEM FOR SETTING AN ACCELERATION SCHEDULE FOR ENGINE START

Herein provided are methods and systems for setting an acceleration schedule for engine start of a gas turbine engine. A rotational acceleration measurement of the engine is obtained after the engine is energized in response to a start request. The rotational acceleration measurement of the engine is compared to a threshold value within an acceleration band having a maximum threshold and a minimum threshold. An acceleration schedule is determined based on a position of the rotational acceleration measurement of the engine in the acceleration band relative to the threshold value. 1. A method for setting an acceleration schedule for engine start of a gas turbine engine , the method comprising:obtaining a rotational acceleration measurement of the engine after the engine is energized in response to a start request;comparing the rotational acceleration measurement of the engine to a threshold value within an acceleration band having a maximum threshold and a minimum threshold; anddetermining an acceleration schedule based on a position of the rotational acceleration measurement of the engine in the acceleration band relative to the threshold value.2. The method of claim 1 , wherein determining an acceleration schedule comprise selecting one of a maximum schedule associated with the maximum threshold and a minimum schedule associated with the minimum threshold as a function of the position of the rotational acceleration measurement of the engine relative to the threshold value.3. The method of claim 1 , wherein the maximum threshold has a maximum acceleration schedule associated thereto and the minimum threshold has a minimum acceleration schedule associated thereto claim 1 , and wherein determining the acceleration schedule comprises selecting values for the acceleration schedule between the maximum acceleration schedule and the minimum acceleration schedule proportional to the position of the rotational acceleration measurement relative to the threshold value.4. The ...

TURBOMACHINE STARTER OIL FILTRATION SYSTEM

A starter configured for use with a turbomachine includes a housing defining a cavity, a transmission operative to convert an airflow into rotational motion for starting an engine, wherein the cavity is configured to hold a quantity of starter oil for lubricating at least a portion of the transmission, and an oil filter disposed in fluid communication with the starter oil. 1. A starter configured for use with a turbomachine , comprising:a housing defining a cavity;a turbine and a transmission operative to convert an airflow into rotational motion for starting an engine, wherein the cavity is configured to hold a quantity of starter oil for lubricating at least a portion of the transmission; andan oil filter disposed in fluid communication with the starter oil.2. The starter of claim 1 , further comprising an oil pressurization system configured to create a pressurized flow of the starter oil or otherwise move the oil to the filter.3. The starter of claim 2 , wherein the transmission includes a gear having gear teeth that are configured to pressurize or move the starter oil.4. The starter of claim 3 , wherein the gear teeth include an airfoil shape.5. The starter of claim 1 , wherein the oil filter is gravity fed.6. The starter of claim 1 , wherein the oil filter includes an external accessible oil filter configured to be removably attached to the housing from outside the housing.7. The starter of claim 6 , wherein the oil filter is a spin-on oil filter.8. The starter of claim 3 , wherein the gear is a ring gear and the gear teeth are speed pickup teeth disposed on the outer diameter of the ring gear.9. The starter of claim 8 , wherein a scoop is disposed within the housing to skim oil from the ring gear as it rotates to pass the oil to the filter.10. The starter of claim 8 , wherein the gear teeth are optimized to maximize oil flow and minimize rotational energy draw from the starter.11. A method for filtering oil in a starter claim 8 , comprising:introducing ...

STARTER OIL QUANTITY INDICATION SYSTEM

A starter can be configured for use with a turbomachine and includes a housing defining a cavity, wherein the cavity is configured to hold a quantity of starter oil, and a temperature sensor disposed within the cavity and configured to sense a temperature within the housing. A system includes a starter for a turbomachine as described herein and a computing apparatus configured to receive signals from the temperature sensor and to determine if the temperature within the housing indicates a sufficient quantity of starter oil. A method for determining oil quantity in a starter includes receiving a temperature signal from a temperature sensor disposed within the starter, determining an oil temperature within the starter based on comparing the temperature signal, and determining if a sufficient amount of oil is present in the starter based on comparing predetermined temperature operational values to the oil temperature. 1. A starter configured for use with a turbomachine , comprising:a housing defining a cavity, wherein the cavity is configured to hold a quantity of starter oil; anda temperature sensor disposed within the cavity and configured to sense a temperature within the housing.2. The starter of claim 1 , wherein the temperature sensor includes a thermocouple.3. The starter of claim 1 , wherein the temperature sensor is disposed in the housing such that the temperature sensor contacts the starter oil when at least a portion of the starter oil is present in the housing.4. The starter of claim 1 , wherein the starter further includes a speed sensor for sensing a rotational speed of at least one rotating component of the starter claim 1 , wherein the temperature sensor is disposed on the speed sensor within the cavity.5. The starter of claim 4 , wherein the speed sensor and the temperature sensor are configured to be connected to a common computing apparatus that is configured to receive and/or interpret signals from the speed sensor and the temperature sensor.6. A ...

ARCHITECTURE FOR A PROPULSION SYSTEM OF A HELICOPTER INCLUDING A HYBRID TURBOSHAFT ENGINE AND A SYSTEM FOR REACTIVATING SAID HYBRID TURBOSHAFT ENGINE

The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine () capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems () for controlling each hybrid turboshaft engine (), each system () comprising an electric machine () connected to the hybrid turboshaft engine () and suitable for rotating the gas generator thereof, and at least one source () of electrical power for said electric machine (), each reactivation system () being configured such that it can drive said turboshaft engine () in at least one operating mode among a plurality of predetermined modes. 1. Architecture of a propulsion system of a multi-engine helicopter having turboshaft engines connected to a power transmission gearbox , the architecture comprising:a hybrid turboshaft engine among said turboshaft engines, the hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter, the other turboshaft engines operating alone during the stable cruise flight;at least two reactivation systems configured to control the hybrid turboshaft engine, each reactivation system comprising an electric machine connected to the hybrid turboshaft engine for rotating said hybrid turboshaft engine, and at least one source of electrical power for said electric machine, each reactivation system configured to drive said hybrid turboshaft engine in at least one operating mode among a plurality of predetermined modes.2. Architecture according to claim 1 , wherein the hybrid turboshaft engine further comprises a gas generator claim 1 , and wherein said plurality of predetermined modes comprises:a rapid reactivation mode, wherein said hybrid turboshaft engine is rotated up to a speed in the range of between 80 and 105% of a nominal ...

Anti-Windmilling Starter Generator

An APU has a gas turbine engine and a starter generator to be selectively driven by the gas turbine engine. A sensor senses windmilling of components associated with the starter generator. A lock feature limits rotation within the starter generator when windmilling is sensed. A method of operation is also disclosed. 1. An auxiliary power unit (APU) comprising:a gas turbine engine, and a starter generator to be selectively driven by said gas turbine engine; anda sensor for sensing windmilling associated with said starter generator, and a lock feature for limiting rotation within said starter generator when windmilling is sensed.2. The APU as set forth in claim 1 , wherein said starter generator is connected into a gearbox claim 1 , and said sensor sensing rotation of a gear within said gearbox.3. The APU as set forth in claim 1 , wherein said starter generator includes a DC powered stator and rotor claim 1 , and said lock feature includes a selective supply of AC power to said stator to limit said rotor from rotation relative to said stator.4. The APU as set forth in claim 3 , wherein a control selectively communicates AC power to said stator only when windmilling is sensed.5. An auxiliary power unit (APU) and air supply system comprising:a gas turbine engine, and a starter generator to be selectively driven by said gas turbine engine;a sensor for sensing undesired rotation of components associated with said starter generator, and a lock feature for limiting rotation of said components within said starter generator when undesired rotation is sensed; andthe lock feature including a supply of AC power into a DC powered stator associated with a DC powered rotor, and a control communicating with said sensor, and receiving a signal when undesired rotation is sensed to supply AC power to said stator.6. The APU and air supply system as set forth in claim 5 , wherein said starter generator is connected into a gearbox claim 5 , and said sensor sensing undesired rotation of a ...

Auxiliary power unit starting system for an aircraft

An auxiliary power unit (APU) starting system for an aircraft comprises an APU comprising a starter motor and a generator, a DC power network, an AC power network, an electric connection line, and a control unit for controlling the APU starting and generating phase. The APU starting system additionally comprises switches for alternatively connecting through the electric connection line the DC power network with the APU starter motor, and the AC power network with the APU generator, wherein the control unit is further configured to operate the switches to connect the DC power network with the APU starter motor during the APU starting phase, and the AC power network with the APU generator during the APU starting phase.

METHOD AND SYSTEM FOR SETTING AN ACCELERATION SCHEDULE FOR ENGINE START

Herein provided are methods and systems for setting an acceleration schedule for engine start of a gas turbine engine. A rotational acceleration measurement of the engine after the engine is energized in response to a start request is obtained. The rotational acceleration measurement of the engine is compared to an acceleration band having a maximum threshold and a minimum threshold. An acceleration schedule is determined based on a position of the rotational acceleration measurement of the engine in the acceleration band. 1. A method for setting an acceleration schedule for engine start of a gas turbine engine , the method comprising:obtaining a rotational acceleration measurement of the engine after the engine is energized in response to a start request;comparing the rotational acceleration measurement of the engine to an acceleration band having a maximum threshold and a minimum threshold; anddetermining an acceleration schedule based on a position of the rotational acceleration measurement of the engine in the acceleration band.2. The method of claim 1 , wherein comparing the rotational acceleration measurement of the engine to the acceleration band comprises determining a ratio of a first difference between the rotational acceleration measurement and the minimum threshold and a second difference between the maximum threshold and the minimum threshold.3. The method of claim 2 , wherein the maximum threshold has a maximum acceleration schedule associated thereto and the minimum threshold has a minimum acceleration schedule associated thereto claim 2 , and wherein determining the acceleration schedule comprises selecting values for the acceleration schedule between the maximum acceleration schedule and the minimum acceleration schedule proportional to the ratio.4. The method of claim 1 , wherein the maximum threshold is a maximum engine core acceleration achieved with a warm engine claim 1 , with a maximum aircraft speed allowed for an engine re-start under a ...

Dirt shield

A system for circumferentially distributing debris in a gas turbine engine includes a component that defines a component cooling channel that has an opening and is configured to receive a cooling airflow. The system also includes a casing at least partially enclosing the component. The system also includes a debris distribution surface positioned radially between the casing and the opening.

Starter/generator

A starter generator located within a sump region of a turbofan engine and coupled to an adapter shaft. The adapter shaft rotationally coupled to the high pressure shaft, forward of a high pressure shaft bearing, and secured by a spanner nut. The engine makes use of two pluralities of electrical conductors, the first extends through an electrical conduit defined by a forward strut extending from the sump region to the outward casing, the second extends axially away from the electric starter. Each of the first plurality of electrical conductors makes reversible contact with a respective one of the second plurality of electrical conductors via an elbow/pin connector, producing a tight turn in area of limited space.

ADDITIVE MANUFACTURING OF ENGINE CONTROL COMPONENT

An example control component for controlling an engine component includes a housing. The housing defines a cavity configured to receive control circuitry configured to control the engine. The housing includes an exterior layer defining an exterior surface of the housing and an interior polymeric layer defining an interior surface of the housing. The interior polymeric layer is adjacent to and substantially coextensive with the exterior layer. The interior polymeric layer includes an electrically and thermally conductive material. An example technique includes forming the exterior layer and forming the interior polymeric layer. 1. A control component for controlling an engine , the control component comprising: an exterior layer defining an exterior surface of the housing; and', 'an interior polymeric layer defining an interior surface of the housing, wherein the interior polymeric layer comprises an electrically and thermally conductive material, and wherein the interior polymeric layer is adjacent to and substantially coextensive with the exterior layer., 'a housing defining a cavity configured to receive control circuitry, the control circuitry being configured to control the engine, the housing comprising2. The control component of claim 1 , wherein the electrically and thermally conductive material comprises one or more of an electrically and thermally conductive polymer claim 1 , a metal claim 1 , or an alloy.3. The control component of claim 2 , wherein the electrically and thermally conductive material comprises the electrically and thermally conductive polymer claim 2 , and wherein the interior polymeric layer further comprises a second polymer different from the electrically and thermally conductive polymer.4. The control component of claim 2 , wherein the interior polymeric layer consists essentially of the electrically and thermally conductive polymer.5. The control component of claim 1 , wherein the exterior layer comprises one or more of a polymer claim ...

SYSTEMS AND METHODS FOR CONTROLLING SURGE MARGIN IN THE COMPRESSOR SECTION OF A GAS TURBINE ENGINE

Systems and methods are disclosed for controlling surge margin in the compressor section of a gas turbine engine. Bypass ports on a first compressor section and second compressor section lead to a bypass conduit. An auxiliary turbine and discharge conduit are positioned in the bypass conduit. Fluid flow from the compressor sections into the bypass conduit via the bypass ports is controlled by bypass control valves. 1. A system for controlling surge margin in a compressor section of a gas turbine engine , the system comprising: one or more compressor stages defining a first compressor section flowpath; and', 'a first compressor section discharge in fluid communication with the first compressor section flowpath;, 'a first compressor section comprisinga first compressor section bypass port positioned along the first compressor section and in fluid communication with the first compressor flowpath; one or more compressor stages defining a second compressor section flowpath, the second compressor section flowpath in fluid communication with the first compressor section flowpath; and', 'a second compressor section discharge in fluid communication with the second compressor section flowpath;, 'a second compressor section comprisinga second compressor section bypass port positioned along the second compressor section and in fluid communication with the second compressor section flowpath;a bypass conduit, extending between the first compressor section bypass port and the second compressor section bypass port;a first compressor section bypass control valve positioned in the bypass conduit downstream of the first compressor section bypass port;a second compressor section bypass control valve positioned in the bypass conduit downstream of the second compressor section bypass port;an auxiliary turbine positioned in the bypass conduit between the first compressor section bypass control valve and the second compressor section bypass control valve;a discharge conduit coupled to and ...

EFFICIENT POWER AND THERMAL MANAGEMENT SYSTEM FOR HIGH PERFORMANCE AIRCRAFT

A system and method for improved system efficiency of an integrated power and control unit (IPCU) of an aircraft is disclosed. The system uses an open-loop cooling system and turbo machine power matching to provide wide operation range without over-sizing. In order to reduce the temperature of the air flow through the cooling heat exchanger, the cooling turbine need to expand further in the same time generating power but the power could be higher than the compressor could absorb so a generator that would convert the power and used in supplying the aircraft would result in more efficient system. 1. A system for providing electrical power and cooling for an aircraft having an engine , the system comprising:an integrated power and control unit (IPCU) starter/generator coupled to a shaft;a cooling turbine coupled to the shaft;a compressor coupled to the shaft between the IPCU starter/generator and the cooling turbine, said compressor having an input for receiving engine bleed air and an output for discharging compressed air while rotating the shaft; anda power summing controller for coupling power from the IPCU starter/generator to a load of the aircraft in parallel with power from the engine.2. The system of claim 1 , further comprising:first and second buses for receiving power from the engine and coupling the power to one or more loads;a third bus for receiving power from the IPCU starter/generator and coupling the power to one or more loads; andfirst and second contactors, coupled to the power summing controller, for coupling the third bus to the first and second buses.3. The system of claim 2 , wherein the first and second contactors further comprise one or more bi-directional solid state claim 2 , high power contactors.4. The system of claim 2 , further comprising:a first integrated control unit (ICU) coupled to the IPCU starter/generator;a first current sensing unit (CSU) receiving an input from the ICU; anda IPCU contactor coupling the first CSU to the third bus ...

CONTROL SYSTEM FOR A GAS TURBINE ENGINE

Systems and methods for shutting down a gas turbine engine in response to a severe mechanical failure include determining a rate of change of one or more process conditions. If the rate of change of the one or more process conditions exceeds a respective predetermined failure threshold, a potential severe mechanical failure of the gas turbine engine may be determined. Steps may be taken to confirm the potential severe mechanical failure of the gas turbine engine. In response, an engine restart is prevented. 1. A method for preventing a gas turbine engine restart in response to a severe mechanical failure , the method comprising:determining a first process condition, or a rate of change of the first process condition, exceeds a first failure threshold, the first failure threshold indicative of a severe mechanical failure of the gas turbine engine;determining a potential severe mechanical failure of the gas turbine engine based at least in part on the determined process condition, or the determined rate of change of the first process condition, exceeding the first failure threshold;confirming the potential severe mechanical failure of the gas turbine engine by determining an accommodation time period following the determined potential severe mechanical failure has not elapsed; andpreventing an engine restart.2. The method of claim 1 , wherein confirming the potential severe mechanical failure of the gas turbine engine further comprises determining the gas turbine engine is operating in sub-idle conditions within the accommodation time period.3. The method of claim 1 , wherein confirming the potential severe mechanical failure of the gas turbine engine further comprises determining the gas turbine engine is operating within a susceptibility window.4. The method of claim 3 , wherein determining the gas turbine engine is operating within the susceptibility window comprises determining the gas turbine engine is operating below a predetermined fire threat flight altitude.5 ...

Systems and Methods for Transferring Mechanical Power in a Turbine Engine

A system (166) for transferring mechanical power in a turbine engine (150/151) including a low pressure spool (162) and a high pressure spool (156) includes a power transfer unit (168) coupled between an output shaft (172) of the low pressure spool (162) and a drive shaft (174) of the high pressure spool (156) to mechanically link the low pressure spool (162) to the high pressure spool (156), and a clutch (170) coupled to the power transfer unit (168), wherein the clutch (170) is configured to transfer power produced from the low pressure spool (162) to the high pressure spool (156).

GEARED GAS TURBINE ENGINE

A gas turbine engine for an aircraft and a method of operating a gas turbine engine on an aircraft. Embodiments disclosed include a gas turbine engine for an aircraft including: an engine core has a turbine, a compressor, and a core shaft; a fan located upstream of the engine core, the fan has a plurality of fan blades; a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; and a gearbox that receives an input from the core shaft and outputs drive to the fan wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of 2 or more than the jet velocity ratio at maximum take-off conditions. 1. A gas turbine engine for an aircraft comprising:an engine core comprising a turbine, and a core shaft connecting the turbine to the compressor;a fan located upstream of the engine core, the fan comprising a plurality of fan blades;a nacelle surrounding the engine core and defining a bypass duct and bypass exhaust nozzle; anda gearbox that receives an input from the core shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the core shaft,wherein the gas turbine engine is configured such that a jet velocity ratio of a first jet velocity exiting from the bypass exhaust nozzle to a second jet velocity exiting from an exhaust nozzle of the engine core at idle conditions is greater by a factor of around 2 or more than the jet velocity ratio at maximum take-off conditions.3. The gas turbine engine of wherein the gearbox has a gear ratio of between around 2.5 and around 5.4. The gas turbine engine of wherein the jet velocity ratio is:within a range from around 0.75 to around 1.3 at cruise conditions; and/orbetween around 2 and 3 at idle conditions; and/orbetween around 0.75 and 1.3, at maximum take-off conditions.5. The ...

SYSTEMS AND METHODS FOR MONITORING AND CONTROLLING A GAS TURBINE ENGINE

A method for controlling a gas turbine engine includes receiving, by a signal processor from a sensor, an operating condition of the gas turbine engine and determining, by the signal processor, whether the operating condition is within an acceptable threshold. In response to the operating condition being outside the acceptable threshold, the method includes restricting, by the signal processor, a subsequent engine restart of the gas turbine engine. Restricting the subsequent engine restart of the gas turbine engine may comprise preventing the subsequent restart. In various embodiments, restricting the subsequent engine restart of the gas turbine engine comprises limiting a subsequent operating state of the gas turbine engine after the subsequent restart. 1. A method for controlling a gas turbine engine in response to a thickness of a lubricant film in a journal bearing of an epicyclic gear system of the gas turbine engine , the method comprising:receiving, by a signal processor from a sensor, an electrical property measurement across the lubricant film;converting, by the signal processor, the electrical property measurement into a calculated lubricant film thickness measurement;determining, by the signal processor, whether the calculated lubricant film thickness measurement is below a predetermined minimum lubricant film thickness; andin response to the calculated lubricant film thickness measurement being below the predetermined minimum lubricant film thickness, restricting, by the signal processor, a subsequent engine restart of the gas turbine engine.2. The method of claim 1 , wherein restricting the subsequent engine restart of the gas turbine engine comprises preventing the subsequent engine restart.3. The method of claim 1 , wherein restricting the subsequent engine restart of the gas turbine engine comprises limiting a subsequent operating state of the gas turbine engine after the subsequent engine restart.4. The method of claim 3 , wherein the subsequent ...

COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION METHOD AND COMPRESSED AIR ENERGY STORAGE AND POWER GENERATION DEVICE

In a compressed air energy storage and power generation device, a compressed air energy storage and power generation method defines, as a reference storage value, a storage value indicating that a storage amount of air in an accumulator tank is in a predetermined intermediate state. At the reference storage value, at least one of a motor and a generator rotates at a rated rotation speed. When a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or less than the rated rotation speed. When the storage value indicating the current storage amount in the accumulator tank is smaller than the reference storage value, at least one of the motor and the generator is controlled to rotate at equal to or more than the rated rotation speed and equal to or less than a maximum permissible rotation speed. 1. A compressed air energy storage and power generation method , comprising:driving an electric motor by fluctuating input power;compressing air by a compressor mechanically connected to the electric motor;storing the compressed air, which is supplied from the compressor, in an accumulator tank;driving an expander by the compressed air supplied from the accumulator tank; andgenerating power by a generator mechanically connected to the expander, whereindefining, as a reference storage value, a storage value indicating that a storage amount of the air in the accumulator tank is in a predetermined intermediate state;at the reference storage value, controlling at least one of the electric motor and the generator to rotate at a rated rotation speed;when a storage value indicating a current storage amount in the accumulator tank is larger than the reference storage value, controlling at least one of the electric motor and the generator to rotate at equal to or less than the rated rotation speed; andwhen the storage value indicating the current ...