ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, СОДЕРЖАЩИЙ СТАРТЕР, УСТАНОВЛЕННЫЙ НА КОРОБКЕ ПРИВОДОВ АГРЕГАТОВ

Изобретение предназначено для газотурбинного двигателя, содержащего коробку приводов агрегатов AGB, механически соединенную с валом двигателя для приведения во вращение вспомогательных агрегатов, и пневматический стартер, установленный на коробке, при этом камеры стартера и коробки сообщаются друг с другом таким образом, чтобы масло для смазки стартера поступало из коробки AGB. Давление в масляной камере стартера создается при помощи источника воздуха, независимого от коробки AGB. Предпочтительно воздух под давлением отбирается из камеры герметизации опорного подшипника двигателя. Такое выполнение газотурбинного двигателя позволит предотвратить утечку масла в нем. 9 з.п. ф-лы, 3 ил.

ВОЗДУШЫЙ СТАРТЕР ДЛЯ ТУРБОДВИГАТЕЛЯ

1. Воздушный стартер для турбодвигателя, включающий в себя: ! - турбину, окруженную передним корпусом (12) стартера, ! - средство передачи мощности турбины, которое окружено задним корпусом (14) стартера, ! - средство (42) жесткого соединения переднего корпуса (12) с задним корпусом (14), ! - тракт (32) потока выходящих газов, предназначенный для переноса воздушного потока от турбины, причем этот тракт потока открыт между задним концом переднего корпуса (12) и передним концом заднего корпуса (14), при этом через этот тракт потока проходит упомянутое средство жесткого соединения (42) и ! - выпускную решетку (44, 60) тракта (32) потока выходящих газов, которая проходит вокруг вала (45) турбины, а передний и задний концы которой содержат средство (48, 52, 62) удерживания в осевом направлении, соответственно, переднего корпуса (12) и заднего корпуса (14) к решетке (44, 60), причем это средство удерживания в осевом направлении предназначено, по меньшей мере, для предотвращения относительного отделения переднего (12) и заднего (14) корпусов, ! отличающийся тем, что, по меньшей мере, упомянутое средство (52, 62) удерживания в осевом направлении одного (14) из корпусов к решетке (44, 60) позволяет относительное вращение решетки (44, 60) и упомянутого корпуса (14). ! 2. Воздушный стартер по п.1, в котором упомянутое средство удерживания в осевом направлении упомянутого корпуса (14) к решетке (44, 60) содержит удерживающее устройство (52, 62), соединенное с соответствующим концом решетки (44, 60) и обращенное к стопорному элементу (38, 68) упомянутого корпуса (14) вдоль осевого направления. ! 3. Воздушный стартер по п.2, в котором упомянутый корпус (14) содержит на своих концах, обращенных к тракту (32)

Anlassvorrichtung fuer Gasturbinen

Andrehvorrichtung fuer Brennkraftmaschinen

A cordite operated starter turbine

... 665,916. Turbines. PLESSEY CO., Ltd. Sept. 29, 1949 [Oct. 1, 1948], No. 25624/48. Class 110(iii). [Also in Groups XXIV and XXVII] A cordite operated starter motor has coaxial contra-rotating wheels connected to a common output shaft through gearing comprising a multiple train of gear wheels arranged on a suitable carrier or support which engages with separate pinions on the concentric shafts. The contra-rotating gas turbine wheels 1, 2 drive a common output shaft 17 through a multiple train of toothed gear wheels. The second stage wheel 2 is mounted on a hollow shaft 6 which carries a pinion 7. This pinion meshes with three gear wheels 10 fixed on three equi-spaced lay shafts 8 which also carry three pinions 11. The pinions 11 drive a ring gear 12 mounted on the output shaft 17. Three countershafts 13 are each fitted with a gear wheel 14 which meshes with a pinion 5 carried by the solid shaft 4 driven by the first stage wheel 1. Gear wheels 15 also carried by the countershafts 13 mesh with ...

PNEUMATIC AND ELECTRO-PNEUMATIC STARTERS

Gas turbine engine buffer seals

Gas turbine engine compressor control method

Improvements in and relating to starting means for gas turbines

... 876,734. Gas turbine plant. ASSOCIATED ELECTRICAL INDUSTRIES Ltd. Feb. 28, 1958 [March 6,1957], No. 7427/57. Class 110 (3). A multiple gas turbine plant starting arrangement comprises a small water content flash boiler, a starter turbine coupled to each gas turbine and a common pressure line with control valves for selective connection between the boiler, starter turbines and similar pressure stages of the compressors of the gas turbines. A number of starter turbines ST 1 , ST 2 are each arranged to start a gas turbine of which one only GT 1 is shown. The starter turbines are connected to their respective gas turbines by clutches SC 1 , SC 2 . A common pressure line PLS is provided to connect corresponding stages of the gas turbines of which GT 1 only is shown and of the starter turbines ST 1 , ST 2 . A flash boiler SGU is connected to the pressure line PLS through a line SCL and control valve MV. Valves STV 1 , STV 2 are provided to control the connection between the common pressure line ...

HIGH ENERGY PARTICLE ARRESTOR FOR AIR TURBINE STARTERS

MULTIFUNCTION INTEGRATED POWER UNIT

MULTIFUNCTION INTEGRATED POWER UNIT A multifunction integrated power unit (MIPU) for use aboard aircraft provides the functions both of an auxiliary power unit and of an emergency power unit while being smaller, lighter, and less expensive than the two units it replaces. Additionally, the integration of both functions in a single unit allows elimination of duplicated service devices and a further reduction in size, cost, and weight in the aircraft itself. The MIPU includes two turbine engines operable under differing conditions, an integrating gear box receiving power from the two engines selectively, and a plurality of accessory devices receiving shaft power from either of the two engines via the gear box.

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.

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 AND ARCHITECTURE FOR THE OPTIMIZED TRANSFER OF POWER BETWEEN AN AUXILIARY POWER MOTOR AND THE MAIN ENGINES OF A HELICOPTER

L'invention vise à optimiser l'ensemble de la motorisation disponible sur un hélicoptère par l'utilisation d'un moteur auxiliaire pour apporter de l'énergie aux équipements et accessoires de l'hélicoptère liés aux moteurs. Dans un exemple d'architecture de transfert d'énergie optimisé pour la mise en uvre de l'invention, les moteurs principaux (1, 1') et le groupe APU (8) comme moteur auxiliaire comportent un générateur de gaz (2; 81) en liaison avec, pour les moteurs principaux (1, 1'), des boîtes de réduction (6)et boîtes accessoires (7) de prises de puissance mécanique, électrique et/ou hydraulique, et en liaison avec, pour le groupe APU (8), au moins un organe de conversion de puissance (83, 84, 11). L'organe de conversion de puissance (83, 84, 11) du groupe APU (8) est relié aux équipements et accessoires à travers la boite de réduction (6) et/ou la boîte accessoire (7) des moteurs principaux (1, 1').

Einrichtung zum Inbetriebsetzen von Wärmekraftanlagen, in welchen ein gasförmiges Arbeitsmittel dauernd einen geschlossenen Kreislauf unter Überdruck beschreibt.

Anlassvorrichtung für Maschinen.

Gasturbinenanlage

Einrichtung zum Anlassen einer Gasturbinenanlage.

Vorrichtung zum Anfahren von Gasturbinenanlagen.

Installation de démarrage comprenant une turbine à gaz

Vorrichtung zum Anlassen einer Gasturbinenanlage mittels einer Anlassturbine

Regeleinrichtung für die Beschleunigung einer Turbine

Hilfsaggregat zum Anwerfen von Strahltriebwerken und zur Abgabe von elektrischer Energie

Dispositif de turbine à gaz de démarrage de propulseur à réaction d'avion

Heissgasgenerator

Transportables Gasturbinenkraftwerk mit Hilfsgasturbinenanlage zum Anlassen der Hauptgasturbinenanlage

Heissgasgenerator

Sofortreserveanlage für elektrisches Leitungsnetz

Notstromgruppe mit einer Gasturbine und mit einem mit dieser gekuppelten Generator

Vorrichtung zur Abgabe von Druckgas an eine pneumatische Anlage eines Luftfahrzeugs

AIR TURBINE STARTER WITH DECOUPLER

DEVICE FOR the STARTING OF the ENGINES Of a PLANE AND the DRIVE OF the ANCILLARY EQUIPMENT

System of starting for gas turbine engines

ENGINE HAS GAS TURBINE INCORPORATING A STARTER GOES UP ON LIMPS HAS GEARS

ARRANGEMENT FOR STARTING AN AIRCRAFT ENGINE AND FOR DRIVING AIRCRAFT AUXILIARY EQUIPMENT

Gas turbine

AIR TURBINE STARTER

METHOD AND ARCHITECTURE OPTIMIZED ENERGY TRANSFER BETWEEN AN AUXILIARY MOTOR POWER AND THE MAIN MOTORS OF HELICOPTER

METHOD FOR SUPPORTING AN IDLE TURBINE ENGINE OF A HELICOPTER AND MULTI-ENGINE PROPULSION SYSTEM ARCHITECTURE OF A HELICOPTER TURBINE ENGINE COMPRISING AT LEAST ONE STANDBY WHICH CAN BE

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

SYSTEM OF LUBRICATION FOR STARTER OF TURBOSHAFT ENGINE

HEATING AN ENGINE LUBRICATION SYSTEM

PROCESS AND SYSTEM FOR STARTING A TURBOMACHINE OF AIRCRAFT BY AND AIR FLOW.

... - Procédé et système de démarrage d'une turbomachine d'aéronef par régulation en temps réel de débit d'air. - Le système de démarrage (1) comporte une boucle de régulation (22) qui régule en temps réel l'ouverture d'une vanne (9) d'une alimentation en air d'une turbine de démarrage (11), en fonction de la vitesse de rotation courante mesurée d'un rotor (2) de la turbomachine (3) et d'une valeur de vitesse prédéterminée, ladite turbine de démarrage (11) étant apte à faire tourner le rotor (2) de la turbomachine (3) en vue du démarrage.

Starter for turbine engines

INTEGRATED STARTER FOR AERIAL VEHICLE

Systems and methods for starting an engine on an aircraft are provided. One example aspect of the present disclosure is directed to an integrated starter for starting an engine on an aircraft. The integrated starter includes an air turbine starter. The integrated starter includes a starter air valve integrated with the air turbine starter. The integrated starter includes a controller configured to control the starter air valve. The starter air valve can be movable between a first position and at least a second position to regulate the flow of fluid into the air turbine starter. An output torque of the air turbine starter can be dependent at least in part on the flow of fluid into the air turbine starter. 1. An integrated starter for starting an engine on an aircraft comprising:an air turbine starter;a starter air valve integrated with the air turbine starter; anda controller configured to control the starter air valve,wherein the starter air valve is movable between a first position and at least a second position to regulate the flow of fluid into the air turbine starter;wherein an output torque of the air turbine starter is dependent at least in part on the flow of fluid into the air turbine starter.2. The integrated starter of claim 1 , wherein the starter air valve comprises one or more valve sensors.3. The integrated starter of claim 2 , where the one or more valve sensors comprise at least one of a pressure gauge claim 2 , a vacuum gauge claim 2 , and a manometer.4. The integrated starter of claim 2 , wherein at least one of the one or more valve sensors is configured to measure a pressure.5. The integrated starter of claim 2 , wherein at least one of the one or more valve sensors is configured to measure a temperature.6. The integrated starter of claim 2 , wherein the starter air valve is further configured to adjust the opening of the starter air valve from a first open percentage to a second open percentage based on signals from the one or more valve sensors ...

MULTI-ENGINE COORDINATION DURING GAS TURBINE ENGINE MOTORING

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode. 1. A system for multi-engine coordination of gas turbine engine motoring in an aircraft , the system comprising:a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.2. The system as in claim 1 , wherein the at least one temperature is a measured core engine temperature or an oil temperature.3. The system as in claim 1 , wherein dry motoring is inhibited when the aircraft is not on the ground.4. The system as in claim 1 , wherein the motoring mode is further determined based on a plurality of performance parameters that are based on one or more of: an ambient condition claim 1 , performance limitations of a compressed air source and each air turbine starter driven by the compressed air source claim 1 , engine drag claim 1 , and parasitic factors.5. The system as in claim 4 , wherein the performance parameters are determined based on one or more of: an ambient air temperature claim 4 , an ambient pressure claim 4 , and an oil temperature.6. The system as is claim 1 , wherein the compressed air source is an auxiliary power unit of the aircraft claim 1 , a ground cart claim 1 , or a cross engine bleed.7. The system as in claim 1 , wherein the controller is further operable to monitor a speed of each of the gas turbine engines when dry motoring is active and switch from the multi-engine dry motoring mode to the single engine dry motoring mode based on one or more of the gas ...

Integrated power unit control apparatus and method

The invention relates to secondary power system apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The invention integrated power unit (IPU) performs the function of both on APU and an EPU, while avoiding the use of hazardous monofuels. The IPU includes a turbine engine operable on pressurized ambient air, or on pressurized stored air, along with jet engine fuel. The structure of a combustion chamber for the engine which is able to use pressurized air from two separate sources; of a control able to selectively operate the engine as an EPU, as an APU, and to effect operating transition from EPU to APU; and of a complete secondary power system with the IPU are all disclosed.

Method for accelerating a gas turbine engine

A method for accelerating a gas turbine engine (10) with an air turbine starter (14) employs sensor data (48, 50) indicative of both starter speed and engine speed to enable speed-synchronized engagement of the starter output shaft (16) with an engine input shaft (18), thereby minimizing clutch damage and engine restart time.

Gas turbine engine assembly and method of assembling same

A method for assembling a gas turbine engine including a core gas turbine engine, a low-pressure turbine, a starter, and a generator is provided. The method includes coupling a starter to the core gas turbine engine, and coupling a generator to the low-pressure turbine.

AIR TURBINE STARTER CONTAINMENT SYSTEM

An air turbine starter having a housing, at least one turbine member, and a containment structure. The housing having an interior surface defining an interior. The at least one turbine member rotatably mounted within the interior and having a plurality of circumferentially spaced blades. The containment band having a radially outer surface, a radially inner surface, at least one layer of metal alloy, and at least one layer of shape memory alloy.

PARALLEL STARTER/GENERATOR AND AIR TURBINE STARTER

STARTER FOR GAS TURBINE

PURPOSE: To shorten the no-load operation time of a starting turbine and improve the starting work efficiency by allowing an adjusting valve for the gas pressure supplied into the starting turbine and the exhaust-gas passage of the starting turbine to communicate through an opening and closing valve. CONSTITUTION: A pressure control valve 3 for the driving gas supplied into a starting turbine 1 and the exhaust-gas conduit 6 for the starting turbine 1 are allowed to communicate through a conduit 26 through a three-way solenoid valve 21. Though the P port and the A port of the three-way solenoid valve 21 communicate during the operation of the starting turbine 1, said A port and a B port communicate when a gas turbine 9 is ignited and the acceleration of the starting turbine 1 is completed, and the control gas in the pressure control valve 3 is discharged into the exhaust gas conduit 6 from the conduit 26, and the pressure control valve 3 is sharply closed. Therefore, the no-load operation ...

СИСТЕМА И СПОСОБ ЭКСТРЕННОГО ЗАПУСКА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА

Предложена система экстренного запуска газотурбинного двигателя, содержащая, по меньшей мере, один газогенератор на твердом ракетном топливе, электрически управляемое устройство воспламенения, вычислительное устройство, связанное с устройством воспламенения, и, по меньшей мере, два независимых стартера, каждый из которых предназначен для запуска одного газотурбинного двигателя, при этом каждый стартер содержит турбину привода вала, предназначенного для соединения с валом соответствующего газотурбинного двигателя, при этом выход газов генератора соединен с входом турбины стартера каждого стартера через один распределительный вентиль, связанный с вычислительным устройством. Описаны также летательный аппарат и способ экстренного запуска газотурбинного двигателя. Технический результат изобретений – упрощение, повышение эффективности и экономичности. 3 н. и 3 з.п. ф-лы, 4 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 660 725 C2 (51) МПК F02C 7/26 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F02C 7/26 (2006.01) (21)(22) Заявка: 2016109790, 12.09.2014 (24) Дата начала отсчета срока действия патента: Дата регистрации: 09.07.2018 19.09.2013 FR 1358996 (43) Дата публикации заявки: 24.10.2017 Бюл. № 30 (45) Опубликовано: 09.07.2018 Бюл. № 19 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 19.04.2016 (56) Список документов, цитированных в отчете о поиске: FR 1207024 A, 12.02.1960. EP (86) Заявка PCT: 2267288 A2, 29.12.2010. FR 1448767 A, 18.03.1966. RU 2224690 C2, 27.02.2004. RU 2005898 C1, 15.01.1994. FR 2014/052263 (12.09.2014) (87) Публикация заявки PCT: R U 2 6 6 0 7 2 5 WO 2015/040310 (26.03.2015) Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, стр. 3, ООО "Юридическая фирма Городисский и Партнеры" (54) СИСТЕМА И СПОСОБ ЭКСТРЕННОГО ЗАПУСКА ГАЗОТУРБИННОГО ДВИГАТЕЛЯ ЛЕТАТЕЛЬНОГО АППАРАТА (57) Реферат: Предложена система экстренного запуска соединения с валом соответствующего газотурбинного ...

СПОСОБ И КОНСТРУКЦИЯ ОПТИМИЗИРОВАННОЙ ПЕРЕДАЧИ ЭНЕРГИИ МЕЖДУ ВСПОМОГАТЕЛЬНЫМ СИЛОВЫМ ДВИГАТЕЛЕМ И ОСНОВНЫМИ ДВИГАТЕЛЯМИ ВЕРТОЛЕТА

Изобретение относится к области авиации, в частности к конструкциям систем силовых установок. Способ передачи энергии между вспомогательным (8) и основными двигателями (1) вертолета состоит в добавлении на некоторых этапах полета к мощности основных двигателей (1) мощности вспомогательного двигателя (8) посредством соединения приводного вала (82) вспомогательного двигателя (8) с приводным валом (25) или валом силовой передачи (31) основного двигателя. Конструкция для передачи энергии включает основные двигатели (1, 1') и APU (вспомогательный двигатель) (8), двигатели (1,1`) содержат газогенератор (2; 81) в соединении с редукторами (6) и коробками 7 приводов вспомогательных агрегатов для отбора механической, электрической и/или гидравлической мощности. APU (8) соединен с механизмом преобразования мощности (83, 84, 11). Механизм преобразования мощности (83, 84, 11) соединен с основным и вспомогательным оборудованием через редуктор (6) и/или коробку (7) приводов вспомогательных агрегатов основных ...

УСТРОЙСТВО И СПОСОБ ПРОВЕРКИ ЦЕЛОСТНОСТИ СИСТЕМЫ БЫСТРОЙ РЕАКТИВАЦИИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ ВЕРТОЛЕТА

Изобретение относится к устройству и способу проверки целостности системы быстрой реактивации газотурбинного двигателя, а также к газотурбинному двигателю, оснащенному таким устройством проверки целостности. Объектами изобретения являются способ и устройство проверки целостности системы быстрой реактивации газотурбинного двигателя (5) вертолета, содержащей пневматическую турбину, механически связанную с упомянутым газотурбинным двигателем (5) и питаемую газом под давлением по команде при помощи пневматического контура (8) питания, чтобы обеспечивать возможность приведения во вращение упомянутого газотурбинного двигателя (5) и его реактивацию, при этом упомянутое устройство проверки отличается тем, что содержит средства (21, 22) отбора воздуха под давлением на газотурбинном двигателе (5), трубопровод (23) доставки этого отбираемого воздуха в упомянутый пневматический контур (8) питания газом упомянутой пневматической турбины, средства определения скорости вращения упомянутой пневматической ...

ПНЕВМАТИЧЕСКОЕ УСТРОЙСТВО БЫСТРОЙ РЕАКТИВАЦИИ ГАЗОТУРБИННОГО ДВИГАТЕЛЯ, СТРУКТУРА СИЛОВОЙ УСТАНОВКИ МНОГОМОТОРНОГО ВЕРТОЛЕТА, ОБОРУДОВАННОЙ ТАКИМ УСТРОЙСТВОМ, И СООТВЕТСТВУЮЩИЙ ВЕРТОЛЕТ

Изобретение относится к устройствам быстрой реактивации газотурбинного двигателя вертолета. Устройство содержит пневматическую турбину, механически связанную с упомянутым газотурбинным двигателем для его приведения во вращение с целью обеспечения его реактивации; пневматический аккумулятор, связанный с упомянутой пневматической турбиной через пневматический контур питания газом под давлением упомянутой пневматической турбины; управляемый пневматический вентиль быстрого открывания, установленный на пневматическом контуре между упомянутым аккумулятором и упомянутой пневматической турбиной и выполненный с возможностью перехода по команде по меньшей мере в одно открытое положение, в котором газ может питать упомянутую пневматическую турбину, или в закрытое положение, в котором упомянутая пневматическая турбина перестает получать питание газом под давлением. 4 н. и 8 з.п. ф-лы, 6 ил.

СПОСОБ И КОНСТРУКЦИЯ ОПТИМИЗИРОВАННОЙ ПЕРЕДАЧИ ЭНЕРГИИ МЕЖДУ ВСПОМОГАТЕЛЬНЫМ СИЛОВЫМ ДВИГАТЕЛЕМ И ОСНОВНЫМИ ДВИГАТЕЛЯМИ ВЕРТОЛЕТА

... 1. Способ оптимизированной передачи энергии между вспомогательным двигателем (8) и основными двигателями (1, 1') вертолета, содержащего основные двигатели, предназначенные обеспечивать тяговую энергию, и вспомогательный двигатель, предназначенный обеспечивать нетяговую энергию, отличающийся тем, что он состоит, на некоторых этапах полета, в добавлении мощности, создаваемой вспомогательным двигателем (8), к мощности, создаваемой основными двигателями (1, 1'), посредством соединения приводного вала (82) вспомогательного двигателя (8) с, по меньшей мере, одним приводным валом (25, 25') и/или валом силовой передачи (31, 31'), по меньшей мере, одного основного двигателя (1, 1') через, по меньшей мере, одно согласование мощности (83, 84, 11).2. Способ передачи энергии по п. 1, в котором соединение приводного вала (82) вспомогательного двигателя (8) с, по меньшей мере, одним основным двигателем (1, 1') выполняют на одном из валов этого основного двигателя, выбранного из приводного вала конструкции ...

ANORDNUNG ZUM ANLASSEN EINES FLUGZEUGTRIEBWERKES UND ZUM BETRIEB DER FLUGZEUGHILFSGERAETE

FLUGZEUGNOTSTROMAGGREGAT.

DE-icing system for a butterfly valve

Improvements relating to fuel-and starting-systems for gas-turbine-engines

... 624,345. Gas turbine plant. BALLANTYNE, D. H. July 4, 1947, No. 17749. [Class 110(iii)] [Also in Group XXVII] A gas turbine plant is started by means of a pressure-fluid motor which may be a turbine 15 operated by the gases from a cordite cartridge 17, or by a liquid energized by those gases, and during starting the pressure fluid causes fuel, accumulated in a cylinder 23, to be delivered to the combustion chambers of the plant. To this end, gases from the cordite cartridge are applied to a piston 30 and, through a hydraulic column in a pipe 26, a piston 24 is moved to force fuel from the cylinder 23 to the injection devices 8. A non-return valve 31 prevents this fuel from being forced back through the normal fuelsupply pump 10. During normal running the cylinder 23 is kept full of fuel. When the starting turbine is operated by a pressure liquid, that liquid may be applied to the piston 24. Specification 615,689 is referred to.

TURBINE ROTOR

Improvements relating to engine starting systems

... 885,542. Gas turbine plants. GARRETT CORPORATION. May 27, 1958 [May 29, 1957], No. 16922/58. Class 110 (3). [Also in Group XXVII] An engine starting system for starting a gas turbine power plant comprises two turbine rotor units mechanically interconnected and arranged to be driven from different sources of motive fluid, means being provided whereby the inlet and outlet of one of the turbine rotors are connected to spaces at substantially the same pressure so that this rotor will act as a compressor to provide a braking effect to prevent overspeeding when the second turbine rotor is being driven. The starter shown comprises a rotor 12 having centripetal-type turbine blades 13 on one face and impulse-type turbine blades 14 on its other face. The rotor comprises a stub shaft 30 mounted in bearings 32, 33 and formed with gear teeth 34 which mesh with gears 35 each mounted on a shaft 36 rotatably mounted in bearings 40, 41 in a fixed casing part. The shafts 36 also carry pinions 42 which engage ...

Improvements relating to jet propulsion apparatus

... 749,176. Gas turbine jet propulsion plant. GENERAL ELECTRIC CO. March 18, 1954 [March 23, 1953], No. 7928/54. Class 110(3) One or more main jet propulsion engines having high energy starting characteristics are started by means of an auxiliary jet propulsion engine having a low energy starting characteristic which feeds pressurized fluid to a starter turbine or turbines releasably connected to the main engines. The plant shown comprises a number of main gas turbine jet propulsion engines B and an auxiliary gas turbine jet propulsion engine A. Engines B are started by air turbines 21 connected thereto by clutches 22. The air turbines are fed from a manifold 30 which is connected to the compressors 13, 23 by conduits 14, 24 containing control valves 25, 26, 27. The engine A is started by an electric motor 11 and brought up to maximum speed with the variable area nozzle 10 closed. The area of the nozzle 10 is then increased and air passed through the conduit 14 and valves 25 to the air turbines ...

ARRANGEMENT FOR STARTING AN AIRCRAFT ENGINE AND FOR DRIVING AIRCRAFT AUXILIARY EQUIPMENT

... 1482460 Gas turbine plant; generating combustion gases under pressure VEREINIGTE FLUGTECHNISCHE WERKE-FOKKER GmbH 31 Oct 1974 [2 Nov 1973 26 Nov 1973] 47197/74 Addition to 1471494 Headings F1G and F1L A turbine for starting an aircraft engine and driving aircraft auxiliary equipment, is driven by gases produced by reacting hypergolically aircraft fuel, JP4 or kerosene, with an additional fuel agent, asymmetrical dimethyl hydrazine, burning the mixture with an oxidant, nitric acid or nitrogen peroxide, and then adding further aircraft fuel to the products prior to their arrival at the turbine. The aircraft fuel may be preheated or vapourized by turbine exhaust gases.

Cabin blower system

Decoupler assembly for engine starter

Improvements in or relating to a gas turbine electric generating set

... 1,125,525. Gas turbine electric generating set. UNITED KINGDOM ATOMIC ENERGY AUTHORITY. Aug. 15, 1967 [Aug.31, 1966], No.38949/66. Headings F1G and F1Q. [Also in Division G6] A gas turbine electric generating set for use in conjunction with a steam turbine plant has ancillary circuits so that the gas turbine set can be driven from a steam circuit of the steam turbine plant. In a steam turbine plant which includes a steam-raising nuclear reactor the gas turbine set may be started under emergency conditions by utilizing the large quantities of stored energy in the form of high temperature high pressure water and steam which are available for a considerable period after shut-down. The residual steam can be used for starting the gas turbine set either by supplying it to nozzles which direct steam on to the gas turbine rotor or to a special starter steam turbine. Normally the supply of steam would be stopped once the gas turbine set has started, but the steam supply could be maintained during ...

Improvements in or relating to magnetic switching circuits

... 773,165. Digital electric calculating-apparatus. WESTERN ELECTRIC CO., Inc. April 27, 1955 [April 27, 1954], No. 12155/55. Class 106 (1). [Also in Group XXXIX] In a circuit employing one or more magnetic cores, one or more advance windings are connected in series with the load which is shunted by a circuit containing one or more output windings, the latter circuit being capable of being blocked by outputs from said output windings to permit the advance pulse. to be effective in the load. In an OR circuit, Fig. 1, the core can be set by either of the input windings 21, 22. If the core is not set then the shunt circuit including the output winding 27 and the diode 28 has low impedance and shunts the load 30 and its diode 31. If the core is set, however, winding 27 produces a pulse which back-biases diode 28 so that the shunt has a high impedance and the advance pulse is effective in load 30. The disposition of the diodes ensures that no spurious output can be obtained due to the pulsing of ...

APPARATUS AND METHOD OF PRODUCING A PRESSURIZED GAS

... 1483259 Gas turbine plant; generating combustion gas under pressure NRG Inc 23 Aug 1974 [24 Aug 1973] 37046/74 Headings F1G and F1L [Also in Division F4] Apparatus for generating cooled combustion gas under pressure comprises respective containers storing liquified inert gas and liquified oxygen, a combustion chamber in which fuel is burnt with the oxygen, and means for mixing the inert gas with the combustion products, the storage pressure of the inert gas acting to pump the oxygen and inert gas from the containers. The combustion products may be used for starting gas turbine engines or powering aircraft emergency services. In one arrangement, the liquid oxygen is stored in a flexible polyester or stainless steel bladder 143 which is itself within a double-walled vacuum vessel 123 storing the inert gas, e.g. nitrogen or helium. The outer wall 131 of vessel 123 is lined with a thermal insulator 135 consisting of alternate layers of aluminium foil and glass fibre. The space between inner ...

GAS-TURBINE ENGINE WITH A ON A TRANSMISSION CASE INSTALLED STARTER DEVICE

ACTUATOR FOR AN AIR TURBINE STARTER VALVE

MAIN PROPULSION ENGINE SYSTEM INTEGRATED WITH SECONDARY POWER UNIT

A main engine mounted auxiliary power unit comprises an auxiliary power unit integrated with a primary gas turbine engine into a single power plant suited for aircraft applications. The auxiliary power unit can be mounted within an engine core compartment of the main engine or at the main engine aft center body. The integration of the auxiliary power unit provides for installation and certification cost savings to the airframes by eliminating the need for mounting an auxiliary power unit to the tail section of the aircraft.

METHOD AND SYSTEM FOR EFFICIENT NONSYNCHRONOUS LNG PRODUCTION USING LARGE SCALE MULTI-SHAFT GAS TUSBINES

A drive system for liquefied natural gas (LNG) refrigeration compressors in a LNG liquefaction plant. Each of three refrigeration compression strings include refrigeration compressors and a multi-shaft gas turbine capable of non-synchronous operation. The multi- shaft gas turbine is operationally connected to the refrigeration compressors and is configured to drive the one or more refrigeration compressors. The multi-shaft gas turbine uses its inherent speed turndown range to start the one or more refrigeration compressors from rest, bring the one or more refrigeration compressors up to an operating rotational speed, and adjust compressor operating points to maximize efficiency of the one or more refrigeration compressors, without assistance from electrical motors with drive-through capability and variable frequency drives.

TURBINE STARTER LUBRICANT COOLING

A cooling system for turbine starter lubricant includes one or more outflow transfer passages (54) extending from the turbine starter (10) to a secondary component (40). At least one heat exchange passage (56) affixed at a first end to an end of an outflow transfer passage (54) of the one or more outflow transfer passages (54), is located in the secondary component (40) having a lower interior temperature than the turbine starter (10). One or more return transfer passages (60) are affixed to a second end of the at least one heat exchange passage (56) and extend from the secondary component (40) to the turbine starter (10). Flowing a volume of starter lubricant (42) through the one or more outflow transfer passages (54), the at least one heat exchange passage (56), and the one or more return transfer passages (60) removes thermal energy from the volume of starter lubricant (42) and returns the volume of starter lubricant (42) to the turbine starter (10).

BRAKE MECHANISM FOR AIR TURBINE STARTER

A brake assembly (44) for an air turbine starter (10) includes a brake cylinder (46) located in the air turbine starter (10). A brake piston (48) is located at least partially within the brake cylinder (46) and slidable therein. A biasing member (50) biases the brake piston (48) toward a turbine wheel (12) of the air turbine starter (10) applying a braking force to the turbine wheel (12) and defining a piston chamber (58) between the turbine wheel (12) and the brake piston (48). A through opening (56) in the brake piston (48) into the piston chamber (58) is configured such that a flow of fluid through the through opening (56) into the piston chamber (58) applies a force to the brake piston (48) sufficient to overcome the bias thereby allowing rotation of the turbine wheel (12).

INTEGRATED POWER UNIT CONTROL APPARATUS AND METHOD

... 2065233 9104397 PCTABS00003 The invention relates to secondary power system (10) apparatus and method for use aboard aircraft in place of conventional auxiliary power units (APU's) and emergency power units (EPU's). The inventive integrated power unit (12) (IPU) performs the function of both on APU and an EPU, while avoiding the use of hazardous monofuels. The IPU (12) includes a turbine engine (20) operable on pressurized ambient air, or on pressurized stored air, along with jet engine fuel. The strucutre of a combustion chamber (26) for the engine (20) which is able to use pressurized air from two separate sources; of a control (18) able to selectively operate the engine (20) as an EPU, as an APU, and to effect operating transition from EPU to APU; and of a complete secondary power system (10) with the IPU (12) are all disclosed.

GAS TURBINE ENGINE POWERED AIRCRAFT ENVIRONMENTAL CONTROL SYSTEM AND BOUNDARY LAYER BLEED

Patent, 13DV-10408 An aircraft gas turbine engine is provided with a starting air turbine that is directly connected through the starter gearbox to the high pressure (HP) shaft and is provided with a means to extract excess energy from engine compressor bleed air, return it to the engine, and to start the engine with compressed air from starting air sources, and to cool and provide compressed air for powering the Environmental Control System (ECS) and using the bleed air for cabin refreshening. The air turbine may be connected to a nacelle boundary layer bleed compressor to bleed boundary layer air from a forward portion of the nacelle to reduce nacelle surface drag. The ECS may be provided with a wing boundary layer bleed means which uses a cooling air fan in the ECS to draw cooling air through the heat exchangers in the ECS pack from the boundary layer air from a forward portion of the aircraft's wing to reduce its surface drag.

ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ, КОТОРЫЙ СОДЕРЖИТ СТАРТЕР, УСТАНОВЛЕННЫЙ НА КОРОБКЕ ПРИВОДОВ АГРЕГАТОВ

Газотурбинный двигатель содержит коробку AGB (12) приводов агрегатов, механически соединенную с валом двигателя для приведения во вращение вспомогательных агрегатов, и пневматический стартер (10, 10'), установленный на коробке. Камеры стартера и коробки соединяются одна с другой таким образом, чтобы масло для смазки стартера поступало из коробки AGB. Давление в смазочной камере стартера (10, 10') создается с помощью источника воздуха, независимого от коробки AGB.

METHOD AND SYSTEM FOR STARTING AN AIRCRAFT TURBOMACHINE BY INSERT AND METHOD FOR AIR-FLOW.

Process of startup of a turbine

Starter for engines

System of starting for engines

Removable starter intended in particular for the engines of aviation

Process and device of starting for aerodynes equipped with alternators

Device of starting to gas turbine

REMOVABLE PACK FOR REACTIVATING A GAS TURBINE ENGINE, SYSTEM ARCHITECTURE OF A HELICOPTER PROPELLANT MULTI-TYPE PACK AND HELICOPTER CORRESPONDING

L'invention concerne un pack amovible de réactivation d'un turbomoteur (6) d'hélicoptère comprenant un générateur (7) de gaz équipé d'un arbre (12) d'entrainement, ledit turbomoteur (6) étant apte à fonctionner dans au moins un régime de veille au cours d'un vol stabilisé de l'hélicoptère, ledit pack amovible comprenant: un boîtier (30) amovible comprenant un arbre (31) de sortie de boîtier ; des moyens (32, 33) commandés d'entrainement en rotation dudit arbre (31) de sortie de boîtier, dits moyens de réactivation dudit turbomoteur; des moyens (14) mécaniques d'accouplement réversible dudit arbre (31) de sortie de boîtier audit arbre (12) d'entrainement dudit générateur de gaz.

IGNITION SYSTEM AND MECHANICAL DRIVE DEVICE THEREFOR

L'invention concerne un système d'allumage d'une charge solide d'un générateur de gaz. Le système d'allumage est caractérisé en ce qu'il comprend un dispositif (124) de pilotage, une diode (130) laser adaptée pour émettre un signal optique en cas de réception d'un ordre de mise à feu, une ligne (140) optique adaptée pour transmettre le signal optique, un dispositif (136) d'armement adapté pour présenter un premier état, dit état désarmé, dans lequel le dispositif (136) d'armement empêche la propagation du signal optique dans la ligne (140) optique, et un deuxième état, dit état armé, dans lequel le dispositif (136) d'armement permet la propagation du signal optique dans la ligne (140) optique, l'état armé étant activé qu'en cas de réception d'un ordre d'armement, et un dispositif (128) d'initiation pyrotechnique comprenant une composition (134) pyrotechnique secondaire, adaptée pour être initiée par ledit signal optique et pour allumer la charge solide du générateur (12) de gaz.

METHOD AND SYSTEM FOR STARTING A CONVEYOR SYSTEM.

... - Procédé et système de démarrage d'une turbomachine d'aéronef. - Le système de démarrage (1) comporte un système de commande (16) commandant une ouverture partielle d'une vanne (9) d'une alimentation en air d'une turbine de démarrage (11), pendant une première phase du démarrage, ladite turbine de démarrage (11) étant apte à faire tourner un rotor (2) de la turbomachine (3) en vue du démarrage, afin d'éviter au rotor (2) de rencontrer des fréquences critiques de la turbomachine (3).

Method for accelerating a gas turbine engine

A method for accelerating a gas turbine engine (10) with an air turbine starter (14) employs sensor data (48, 50) indicative of both starter speed and engine speed to enable speed-synchronized engagement of the starter output shaft (16) with an engine input shaft (18), thereby minimizing clutch damage and engine restart time.

Power unit fuel pressurization system

A power generating unit in accordance with the present invention comprises a pressurized gas source (44) providing pressurized gas containing oxygen to be used in combustion of a fuel; a combustor (42) for providing pressurized gas produced by combustion of a mixture of the pressurized gas provided to the combustor by the pressurized gas source and fuel provided to the combustor by a fuel supply (48); a first turbine (68) driven by pressurized gas produced by the combustor; a gear box (70) driven by the turbine having an output shaft (72); a fuel pump (46) disposed within the fuel supply having a pair of input shafts (64 and 76) for providing pressurized fuel to the combustor in response to rotation of either of the input shafts; a motor (58) coupled to the pressurized gas source having a drive shaft (60) which rotates in response to the pressurized gas applied from the gas source; and a coupling mechanism (62 and 74), coupled to the shafts, for applying driving torque to the fuel pump ...

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 containment screen is located within the housing downstream of the at least one turbine member. 1. An air turbine starter for starting an engine , comprising:at least one turbine member that is rotatable about a rotational axis;a housing defining an interior and an exterior and having a portion thereof radially surrounding the at least one turbine member and defining a pathway along which a flow of gas passes there through to interact with the at least one turbine member; anda containment screen located within the interior downstream of the at least one turbine member.2. The air turbine starter of wherein the housing includes a peripheral wall defining the interior and the exterior.3. The air turbine starter of wherein the containment screen abuts the peripheral wall.4. The air turbine starter of wherein the housing further includes an inlet and a set of outlets claim 2 , the set of outlets formed in the peripheral wall claim 2 , and the at least one turbine member is located there between.5. The air turbine starter of wherein the containment screen is located axially between the at least one turbine member and the set of outlets.6. The air turbine starter of wherein the set of outlets includes a plurality of apertures located in the peripheral wall.7. The air turbine starter of wherein the plurality of apertures are circumferentially spaced about the peripheral wall.8. The air turbine starter of wherein the containment screen ...

PLANET SHAFT RETENTION IN PLANETARY GEAR SYSTEM

A planet shaft for supporting a planet gear has a supporting portion extending along a central axis and having a first outer diameter. A flange is formed at one end of the supporting portion, which has a smaller section formed about a portion of a circumference around the central axis, and an enlarged portion extending away from the central axis for a greater distance than the smaller portion. A hole to receive a lock member is formed in the enlarged portion. A planetary gear assembly including such a planet shaft is disclosed as is an air turbine starter including the planetary gear system. Further, a method of installing a planet gear and planet shaft is also disclosed and claimed.

GAS TURBINE WITH LUBRICANT AND FUEL SUPPLY SYSTEMS THEREFOR

PARALLEL STARTER / GENERATOR AND AIR TURBINE STARTER

A system for starting a turbine engine is provided. The system may comprise a gearbox, an electric starter, and an air turbine starter. The gearbox may have a gearbox input shaft. The gearbox may be coupled to the turbine engine. The gearbox input shaft may be coupled to a spool of the turbine engine. The electric starter may have an electric-starter shaft. The electric-starter shaft may be coupled to the gearbox input shaft. The air turbine starter may have an air-turbine-starter shaft. The air-turbine-starter shaft may be coupled to the gearbox input shaft. The electric-starter shaft and the air-turbine-starter shaft may be radially displaced, circumferentially displaced, or both radially and circumferentially displaced, with respective to an axis of the turbine engine, from one another. The electric starter may be a starter-generator connected alternatively between an auxiliary power source and an auxiliary load. 1. A system for starting a turbine engine , comprising:a gearbox having a gearbox input shaft, said gearbox being coupled to said turbine engine and the gearbox input shaft coupled to a spool of the turbine enginean electric starter having an electric-starter shaft coupled to said gearbox input shaft;an air turbine starter having an air-turbine-starter shaft coupled to said gearbox input shaft; andwherein said electric-starter shaft and said air-turbine-starter shaft are radially displaced, circumferentially displaced, or both radially and circumferentially displaced, with respective to an axis of the turbine engine, from one another; and wherein and the electric starter is a starter-generator connected alternatively between an auxiliary power source and an auxiliary load.2. The system of claim 1 , further comprising a second gearbox coupling both of said electric-starter shaft and air-turbine-starter shaft to said gearbox input shaft.3. The system of claim 2 , wherein said second gearbox has a first gear ratio between said electric-starter shaft and ...

Air turbine starter with turbine air exhaust outlet valve

A system includes an air turbine starter having an inlet, a turbine air exhaust outlet, an output shaft, and a turbine in fluid communication with the inlet and the turbine air exhaust outlet. The turbine is operably coupled to the output shaft. The system also includes an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet.

Air turbine starter inlet housing assembly airflow path

An inlet housing assembly for an Air Turbine Starter includes an outer flowpath curve of an inlet flowpath defined by a multiple of arcuate surfaces in cross-section.

Air turbine starter turbine blade airfoil

A blade profile section for an Air Turbine Starter includes an airfoil which defines an airfoil profile section through a leading edge and a trailing edge. The airfoil profile section is defined by a set of X-coordinates and Y-coordinates defined in any of Table I, Table II, Table III or Table IV scaled by a desired factor. The X-coordinate is the tangential direction, the Y-coordinate is the axial direction, and the Z-coordinate is a radial direction between an airfoil root and an airfoil tip.

Anti-rotation for thrust washers in planetary gear system

A bushing for use in a planetary gear system has a cylindrical body portion defining a bore extending along a central axis to be received on a planetary gear shaft. A tab extends axially beyond a nominal body portion of the bushing and is received in a notch in a thrust washer adjacent to the bushing to prevent rotation of the thrust washer. A gear cage and an air turbine starter incorporating the bushing, along with a method of installing the bushing are also disclosed.

Multi-spool intercooled recuperated gas turbine

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

AIR TURBINE STARTER WITH TURBINE AIR EXHAUST OUTLET VALVE

A system includes an air turbine starter having an inlet, a turbine air exhaust outlet, an output shaft, and a turbine in fluid communication with the inlet and the turbine air exhaust outlet. The turbine is operably coupled to the output shaft. The system also includes an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet. 1. A system comprising: an inlet;', 'a turbine air exhaust outlet;', 'an output shaft; and', 'a turbine in fluid communication with the inlet and the turbine air exhaust outlet, the turbine operably coupled to the output shaft; and', 'an outlet valve assembly configured to adjust an exhaust area of the turbine air exhaust outlet., 'an air turbine starter comprising2. The system as in claim 1 , further comprising an actuator in fluid communication with the outlet valve assembly claim 1 , the actuator operable to adjust the exhaust area of the turbine air exhaust outlet.3. The system as in claim 2 , wherein the outlet valve assembly further comprises:a valve housing; anda valve body arranged between the valve housing and the turbine air exhaust outlet.4. The system as in claim 3 , wherein the valve housing comprises at least one pressure port claim 3 , and a pressurized cavity is formed between the at least one pressure port and the valve body responsive a pressurized flow from the actuator.5. The system as in claim 4 , further comprising at least one spring positioned between a housing of the air turbine starter and the valve body claim 4 , the at least one spring configured to provide an opening force to slide the valve body towards an open position and increase the exhaust area of the turbine air exhaust outlet.6. The system as in claim 5 , wherein the actuator is operable to increase the pressurized flow to the pressurized cavity and provide a closing force greater than the opening force to slide the valve body towards a closed position and decrease the exhaust area of the turbine air exhaust outlet.7. ...

METHOD FOR ASSISTING A TURBOSHAFT ENGINE IN STANDBY OF A MULTIPLE-ENGINE HELICOPTER, AND ARCHITECTURE OF A PROPULSION SYSTEM OF A HELICOPTER COMPRISING AT LEAST ONE TURBOSHAFT ENGINE THAT CAN BE IN STANDBY

The invention relates to an architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines (), characterised in that it comprises: at least one hybrid turboshaft engine () that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines () operating alone during this stable flight; an air turbine () that is mechanically connected to the gas generator () of the hybrid turboshaft engine () and is suitable for rotating said gas generator (); means for withdrawing pressurised air from the gas generator () of a running turboshaft engine (); and a duct () for routing this withdrawn air to said air turbine (). 1. Architecture of a propulsion system of a multiple-engine helicopter comprising turboshaft engines , each turboshaft engine comprising a gas generator and a free turbine that is rotated by the gases from said gas generator , wherein said system comprises:at least one turboshaft engine from among said turboshaft engines, referred to as the hybrid turboshaft engine, that is capable of operating in at least one standby mode during a stable flight of the helicopter, the other turboshaft engines, referred to as running turboshaft engines, operating alone during this stable flight,an air turbine that is mechanically connected to said gas generator of said hybrid turboshaft engine,means for withdrawing pressurised air from the gas generator of a running turboshaft engine,a duct for routing this withdrawn air to said air turbine such that the air turbine can transform the energy from said pressurised air into mechanical energy that drives said gas generator of said hybrid turboshaft engine.2. Architecture according to claim 1 , wherein said means for withdrawing air from the gas generator of a running turboshaft engine comprise a withdrawal port that is arranged on a compressor of this running turboshaft engine.3. Architecture according to claim 1 , wherein said air ...

AIR TURBINE START SYSTEM

An air turbine starter device comprises a rotor arranged in a cavity of a housing, a first manifold having a cavity with a port operative to direct compressed air to the rotor, a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold. 1. An air turbine starter device comprising:a rotor arranged in a cavity of a housing;a first manifold having a cavity with a port operative to direct compressed air to the rotor;a second manifold having a cavity with a port operative to direct compressed air to the rotor, wherein the first manifold is larger than the second manifold.2. The device of claim 1 , wherein the first manifold includes a greater number of ports than a number of ports in the second manifold.3. The device of claim 1 , wherein the cavity of the first manifold defines a first compressed air flow path that flows through the cavity of the first manifold claim 1 , through the port of the first manifold claim 1 , and through a nozzle that is communicative with the cavity of the housing.4. The device of claim 1 , wherein the cavity of the second manifold defines a second compressed air flow path that flows through the cavity of the second manifold claim 1 , through the port of the second manifold claim 1 , and through a nozzle that is communicative with the cavity of the housing.5. The device of claim 1 , wherein the rotor is operative to rotate when compressed air impinges on the rotor.6. The device of claim 1 , wherein the rotor is mechanically linked to a gas turbine engine such that the rotation of the rotor rotates components of the gas turbine engine.7. The device of claim 1 , wherein the air turbine starter is communicatively connected to a compressed air source.8. An air turbine starter system claim 1 , the system comprising: a rotor arranged in a cavity of a housing;', 'a first manifold having a cavity with a port operative to direct compressed air to the rotor ...

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 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;a steam turbine that is driven by steam generated by the heat recovery steam generator; anda 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.2. The combined cycle plant according to claim 1 , wherein a first output change mode in which 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; and', 'a second output change mode in which 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, and, 'the control device hasthe control device is capable of selectively switching between the first output change mode and the second output change mode according to a switching signal.3. The combined cycle plant according to claim ...

AIR TURBINE STARTER AND STARTING METHOD THEREOF

An air turbine starter (ATS) assembly includes a rotatable pinion gear () wherein the rotatable pinion gear is coupled to a combustion engine (), a speed sensor () measuring the rotational speed () of the rotatable pinion gear (), a torque sensor () providing a torque output () indicative of a torque experienced by the pinion gear (), and a controller module configured to operate a starting sequence for the ATS assembly such that the rotational speed () is controllably increased while the torque output () is kept below the start sequence torque threshold (). 1. A method of starting a combustion engine started with a starter , the method comprising:during a start sequence of the combustion engine, monitoring, by a controller module, a speed parameter indicative of a rotational speed of the starter rotationally coupled with the combustion engine and a torque parameter indicative of a torque of the starter;determining, in the controller module, whether the monitored speed parameter exceeds a corresponding speed value included in a start sequence speed profile and whether the monitored torque parameter exceeds a start sequence torque threshold; andin response to determining the monitored speed parameter does not exceed the corresponding speed value of the start sequence speed profile and the monitored torque parameter does not exceed the start sequence torque threshold, controllably increasing the rotational speed of the starter by the controller module such that the increasing prevents the monitored torque parameter from satisfying the start sequence torque threshold.2. The method of wherein the monitoring the torque parameter includes monitoring the torque experienced by a pinion gear of the starter.3. The method of further comprising determining whether the monitored speed parameter exceeds a target rotational speed prior to expiration of a target period of time.4. The method of claim 3 , further comprising determining whether the monitored speed parameter exceeds a ...

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 ...

Foil-air bearing assembly for engine starter

An air turbine starter that includes a turbine member for rotatably extracting mechanical power from a flow of fluid, where the turbine member is coupled to a drive shaft to provide a rotational output. The air turbine starter further includes a foil-air bearing assembly and a thrust bearing that rotatably support the drive shaft.

Air Turbine Starter with Integrated Motor for Main Engine Cooling

An air turbine starter (ATS) includes a support structure and a turbine. The ATS additionally includes a gear train that is configured for receiving torque input from the turbine. The gears include an integrated input gear. The ATS further includes an output member. The output member is operably coupled to the gear train and a main engine input member. The output member is configured to transfer torque from the gear train to the main engine input member. Additionally, the ATS includes a motor system that is supported by the support structure. The motor system includes a motor and a motor output gear. The motor output gear is configured to engage the integrated input gear for selectively delivering motor torque from the motor to the integrated input gear such that the motor torque transfers to the main engine input member to selectively dry motor the main engine at a predetermined speed. 1. An air turbine starter for a main engine , the main engine including a main engine input member , the air turbine starter comprising:a support structure;an airflow passage extending at least partially through the support structure;a turbine that is supported by the support structure for rotation relative to the support structure, the turbine configured to be driven in rotation due to air flowing through the airflow passage;a gear train that is operably coupled to the turbine and configured for receiving turbine torque input from the turbine, the plurality of gears including an integrated input gear;an output member that is supported by the support structure for rotation relative to the support structure, the output member being operably coupled to the gear train and the main engine input member, the output member being configured to transfer torque from the gear train to the main engine input member; anda motor system that is supported by the support structure, the motor system including a motor and a motor output gear, the motor output gear configured to engage the integrated ...

AIR TURBINE STARTER WITH PRIMARY AND SECONDARY AIR FLOW PATHS

An air turbine starter that includes a housing. The housing can circumscribe a turbine coupled that is coupled to a gear train in a gear box via a drive shaft. A primary air flow path is defined between a primary inlet and a primary outlet. Air in the primary air flow path can flow into a secondary air flow path or rotate the turbine, that converts energy from the air flow to rotational mechanical energy. Air in the secondary air flow path can pass through at least a first cavity and first passage before rejoining the primary air flow or joining ambient air. 1. An air turbine starter comprising:a housing defining an interior having a primary inlet and a primary outlet to define a primary air flow path from the primary inlet to the primary outlet;a stator located in the interior that defines at least a portion of the primary air flow path, where the stator includes a hub with a plurality of circumferentially spaced vanes that include a root and a tip to define a span-wise direction;a first passage extending from the root to the tip of at least one of the plurality of circumferentially spaced vanes;a turbine located in the interior downstream of the stator and including a rotor, with a plurality of circumferentially spaced blades extending into the primary air flow path;a first cavity defined by a forward face of the rotor and a rear face of the hub; anda secondary air flow path that fluidly connects the first cavity with either the primary air flow path downstream of the turbine or ambient air, wherein the secondary air flow path is at least partially defined by the first passage.2. The air turbine starter of claim 1 , wherein the first passage is at least two physically distinct passages fluidly connecting the root to the tip.3. The air turbine starter of claim 1 , further comprising a second passage fluidly connecting the first cavity to the primary air flow path downstream of the turbine.4. The air turbine starter of claim 1 , wherein the first passage of the at ...

TURBINE ENGINE AND METHOD OF COOLING

A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine may include performing a plurality of motoring cycles. The plurality of motoring cycles may include receiving feedback on a temperature within a turbine engine in a post-shutdown state, actuating a starter motor when the temperature is greater than a predetermined threshold, operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine, and shutting down the starter motor after the motoring time. 120-. (canceled)21. A method of mitigating thermal rotor bow in a rotor assembly of a turbine engine , the method comprising:performing a plurality of motoring cycles, the plurality of motoring cycles comprising:receiving feedback on a temperature within a turbine engine in a post-shutdown state;actuating a starter motor when the temperature is greater than a predetermined threshold;operating the starter motor for a motoring time to exhaust some residual heat from the turbine engine; andshutting down the starter motor after the motoring time.22. The method of claim 21 , wherein the motoring time comprises a predetermined duration.23. The method of claim 21 , wherein operating the starter motor for the motoring time comprises operating the starter motor until the temperature is reduced below a second predetermined threshold.24. The method of claim 21 , comprising:receiving feedback on a running time of the turbine engine; andperforming the plurality of motoring cycles if the running time of the turbine engine is greater than a predetermined running time-threshold.25. The method of claim 21 , wherein actuating the starter motor comprises:actuating the starter motor at a preset time after a full stop command corresponding to the post-shutdown state.26. The method of claim 25 , wherein the preset time allows some thermal rotor bow to form before actuating the starter motor.27. The method of claim 21 , comprising:allowing some thermal rotor bow to form when ...

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.

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 box includes a gear train coupled with the turbine member. A gear box housing at least partially defines an interior having an open face and a body at least partially closes the open face. 1. An air turbine starter , comprising:a housing;at least one turbine member journaled within the housing;a gear box at least partially defining an interior having an open face and where the interior at least partially houses a gear train that is drivingly coupled with the at least one turbine member;a retainer having a body at least partially closing the open face; andan output shaft operably coupled with the gear train and having an output end.2. The air turbine starter of wherein the retainer includes a plate that spans at least a portion of the open face.3. The air turbine starter of wherein the plate is non-planar.4. The air turbine starter of wherein the plate includes a peripheral portion mounted between the housing and the gear box.5. The air turbine starter of wherein the plate includes a central portion that extends into the housing.6. The air turbine starter of wherein the plate includes an aperture within the central portion.7. The air turbine starter of claim 6 , further comprising a drive shaft operably coupled between the at least one turbine member and the gear train and passing through the aperture.8. The air turbine starter of wherein the body further includes a peripheral portion mounted to at least one of the housing or the gear box.9. The air turbine starter of wherein the body further includes a peripheral portion mounted between the housing and the gear box.10. The air turbine starter of claim 1 , further ...

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.

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.

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. 1. An air turbine starter , comprising:a housing defining a periphery and having an inlet, a set of outlets located circumferentially spaced about the periphery, and a flow path extending between the inlet and the set of outlets for communicating a flow of gas there through; anda turbine member journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas.2. The air turbine starter of wherein the set of outlets is located in a mid-section of the air turbine starter.3. The air turbine starter of wherein the periphery is defined by a peripheral wall.4. The air turbine starter of wherein the peripheral wall is cylindrical.5. The air turbine starter of wherein the set of outlets is circumferentially spaced about 360 degrees of the peripheral wall.6. The air turbine starter of wherein the set of outlets is in pairs circumferentially spaced about the periphery.7. The air turbine starter of wherein the set of outlets includes outlets of differing sizes.8. The air turbine starter of wherein the set of outlets is in pairs circumferentially spaced about the periphery.9. The air turbine starter of wherein one aperture of a pair of the set of outlets has a differing size from another aperture of the pair.10. An air turbine starter claim 8 , comprising:a housing including a peripheral wall having an inlet, a set of outlets located substantially 360 degrees about the peripheral wall, and a flow path extending between the inlet and the set of outlets for communicating a flow of gas there through.11. The air turbine starter of wherein the set of outlets is located in an ...

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 secondary supply port is fluidly coupled to the flow of the pressurized gas in the housing. 1. An air turbine starter , comprising:a housing defining an inlet configured to receive pressurized gas, an outlet, and a flow path extending between the inlet and the outlet for communicating a flow of the pressurized gas there through; anda secondary supply port fluidly coupled to the flow of the pressurized gas in the housing and adapted to provide a secondary supply of the pressurized gas from the housing.2. The air turbine starter of wherein the housing comprises multiple sections operably coupled together including an inlet section and a turbine section.3. The air turbine starter of wherein the inlet section further comprises an inlet assembly mounted to the turbine section and forms at least a portion of the inlet.4. The air turbine starter of wherein the inlet assembly includes an inlet coupling adapted to couple with a conduit and receive pressurized gas therefrom.5. The air turbine starter of wherein the secondary supply port is included in the inlet assembly and located fluidly downstream of the inlet coupling.6. The air turbine starter of wherein the inlet assembly further includes an inlet plenum fluidly coupled to the inlet coupling.7. The air turbine starter of wherein the secondary supply port is included in the inlet assembly and fluidly couples with the inlet plenum.8. The air turbine starter of wherein the inlet assembly further includes an inlet valve moveable between a closed position and an opened position and adapted to fluidly couple the inlet plenum and the turbine section when in the opened position.9. ...

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. 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, the housing having a diameter that is less than 15.63 cm (6.15 inches); anda set of turbine members journaled within the housing and disposed within the flow path for rotatably extracting mechanical power from the flow of gas.2. The air turbine starter of wherein the set of turbine members comprises a first rotor and a second rotor defining a first stage and a second stage claim 1 , respectively.3. The air turbine starter of claim 2 , further comprising a first stator upstream of the first rotor and wherein the first stator includes 16 nozzles.4. The air turbine starter of claim 3 , further comprising a second stator upstream of the second rotor and wherein the second stator includes 25 nozzles.5. The air turbine starter of wherein the outlet comprises a plurality of apertures located downstream of the set of turbine members.6. The air turbine starter of wherein the plurality of apertures are circumferentially spaced about the housing.7. The air turbine starter of wherein the diameter of the housing is 14.6 cm (5.75 inches).8. The air turbine starter of claim 1 , further comprising an inlet assembly mounted to a first end of the housing and a gear box mounted to a second end of the housing claim 1 , the gear box at least partially housing a gear train drivingly coupled with the set of turbine members.9. The air turbine starter of claim 8 , further comprising a drive shaft operably coupled with the gear train and ...

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.

AIR TURBINE STARTER WITH NOZZLE RETENTION MECHANISM

An air turbine starter having a housing defining an interior with a primary inlet and a primary outlet to define a primary air flow path from the primary inlet to the primary outlet. A nozzle is located within the interior and has circumferentially spaced vanes. A shroud is also located within the interior and circumscribes at least a portion of the vanes. A retention mechanism constrains the axial movement of nozzle.

DECOUPLER ASSEMBLY 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 train 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 train operably coupled with the gear train and configured to provide a rotational output; and a drive hub operably coupled to the drive train and having a first set of teeth;', 'an output shaft having a first end having a second set of teeth configured to mate with the first set of teeth and a second end selectively operably coupled to the engine, the second set of teeth allow for driving torque transfer from the drive hub to the output shaft and the second set of teeth slide on the first set of teeth when back driving torque is transmitted such that the output shaft is moved axially away from the drive hub;', 'a shear pin operably coupled at a first end to the drive hub and operably coupled at a second end to the output shaft and having a shear fuse; and', 'a sheath surrounding at least a portion of the shear pin and axially moveable along a portion of the shear pin;', 'a load path for torque transmission through the drive hub and output shaft occurs during normal operation; and, 'a decoupler assembly, ...

Air Turbine Starter Matched Set Gear Cage Alignment Feature

A gear cage assembly configured to support a plurality of planet gear in an air turbine starter is provided including a main plate and a back plate. The main plate includes a plurality of legs that extend from a first surface. A pin protrudes from a one of the plurality of legs. A plurality of shallow openings formed in the first surface extends over only a portion of a depth of the main plate. The back plate includes a plurality of bearing holes substantially identical to the plurality of shallow openings. A biasing mechanism and at least one alignment feature protrude from the back plate. The at least one alignment feature and the biasing mechanism are configured to contact at least one of the plurality of legs. A bushing mounted within the back plate is configured to receive the pin.

Method for detecting a fluid leak in a turbomachine and fluid distribution system

A method for detecting a high temperature fluid leak in a turbomachine. The turbomachine includes a source of high temperature pressurized fluid, at least one fluid distribution line suitable for distributing said high temperature fluid, and a turbomachine compartment wherein the distribution line is at least partially housed. The method includes measuring at least two pressure parameters of the turbomachine compartment, including a measured pressure and a pressure variation over time; detecting a high temperature fluid leak when at least one of the two pressure parameters of the turbomachine compartment reaches a characteristic value of a high-temperature fluid leak in the compartment. A high-temperature fluid distribution system and a turbomachine comprising such a high temperature fluid distribution system.

HYBRID GAS TURBOFAN POWERED SUB-IDLE DESCENT MODE

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

AIR TURBINE START SYSTEM

An air turbine starter device includes a gear assembly, a rotor arranged in a cavity of a housing and operably connected the gear assembly, a first manifold having a cavity with a first manifold port operative to direct compressed air to the rotor, and a second manifold having a cavity with a second manifold port operative to direct compressed air to the rotor. The first manifold is larger than the second manifold, the second manifold is fluidly connected in parallel with the first manifold, and the first manifold port and the second manifold port are operative to drive the rotor in a common direction for starting a gas turbine connected to the gear assembly. Air turbine starter systems and methods of starting gas turbine engines are also described. 1. An air turbine starter device comprising:a gear assembly;a rotor arranged in a cavity of a housing, wherein the rotor is operably connected the gear assembly;a first manifold having a cavity with a first manifold port operative to direct compressed air to the rotor; anda second manifold having a cavity with a second manifold port operative to direct compressed air to the rotor,wherein the first manifold is larger than the second manifold, wherein the second manifold is fluidly connected in parallel with the first manifold, and wherein the first manifold port and the second manifold port are operative to drive the rotor in a common direction.2. The device of claim 1 , wherein the first manifold includes a greater number of ports than a number of ports in the second manifold.3. The device of claim 1 , wherein the cavity of the first manifold defines a first compressed air flow path that flows through the cavity of the first manifold claim 1 , through the port of the first manifold claim 1 , and through a nozzle that is communicative with the cavity of the housing.4. The device of claim 1 , wherein the cavity of the second manifold defines a second compressed air flow path that flows through the cavity of the second ...

INTERCOOLED COOLING AIR USING COOLING COMPRESSOR AS STARTER

A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. The cooling compressor is connected to be driven with at least one rotor in the main compressor section. A source of pressurized air is selectively sent to the cooling compressor to drive a rotor of the cooling compressor to rotate, and to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine. An intercooling system is also disclosed. 1. A gas turbine engine comprising;a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations;a turbine section having a high pressure turbine;a tap connected for tapping air from at least one of the more upstream locations in the compressor section, and connected for passing the tapped air through a heat exchanger and then to a cooling compressor, the cooling compressor for compressing air downstream of the heat exchanger, and delivering air into at least one of the high pressure turbine and the high pressure compressor;the cooling compressor being connected to be driven with at least one rotor in the main compressor section, and a source of pressurized air that is selectively sent to the cooling compressor, to drive a rotor of the cooling compressor to rotate, to in turn drive the at least one rotor of the main compressor section at start-up of the gas turbine engine; andwherein the rotor of the cooling compressor includes a centrifugal compressor impeller.2. The gas turbine engine as set forth in claim 1 , wherein air temperatures at the ...

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 ...

AIR TURBINE STARTER INCLUDING A LIGHTWEIGHT, LOW DIFFERENTIAL PRESSURE CHECK VALVE

An air turbine starter includes a starter housing and a check valve. The check valve is disposed within the starter housing and is configured, in response to a pressure differential across the check valve, to selectively allow and prevent lubricant to flow therefrom. The check valve includes a valve includes a valve body, a valve seat, a valve bore, a valve element, and a plurality of rounded grooves. The valve bore is formed in the valve body between the valve seat and the lubricant outlet port. The valve element is disposed within the valve bore and is movable between a plurality of open positions and a closed position. The rounded grooves are formed in the valve body, and are disposed adjacent to, and in fluid communication with, the valve bore to improve lubricant to flow past the valve element when the valve element is in an open position. 1. An air turbine starter , comprising:a starter housing including a lubricant supply opening and a lubricant discharge opening, the lubricant supply opening adapted to receive lubricant from a lubricant source, the lubricant discharge opening configured to supply lubricant from the starter housing to the lubricant source; anda check valve disposed within the starter housing proximate the lubricant discharge opening, the check valve configured, in response to a pressure differential across the check valve, to selectively allow and prevent lubricant to flow from the starter housing and through the discharge opening, a valve body including a lubricant inlet port and a lubricant outlet port, the lubricant inlet port adapted to receive a flow of lubricant, the lubricant outlet port in fluid communication with the lubricant discharge opening,', 'a valve seat formed in the valve body and disposed between the lubricant inlet port and the lubricant outlet port, the valve seat having an opening formed therein,', 'a valve bore formed in the valve body between the valve seat and the lubricant outlet port,', 'a valve element disposed ...

GAS TURBINE ENGINE MOTORING WITH STARTER AIR VALVE MANUAL OVERRIDE

A system for gas turbine engine motoring includes an air turbine starter coupled to a gearbox of a gas turbine engine and a starter air valve in fluid communication with the air turbine starter to drive motoring of the gas turbine engine responsive to a regulated pressure from a compressed air source. A manual override of the starter air valve is adjustable to one or more predefined intermediate positions that partially open the starter air valve to limit a motoring speed of the gas turbine engine below a resonance speed of a starting spool of the gas turbine engine responsive to the regulated pressure. 1. A system for gas turbine engine motoring , the system comprising:an air turbine starter coupled to a gearbox of a gas turbine engine;a starter air valve in fluid communication with the air turbine starter to drive motoring of the gas turbine engine responsive to a regulated pressure from a compressed air source; anda manual override of the starter air valve, the manual override adjustable to one or more predefined intermediate positions that partially open the starter air valve to limit a motoring speed of the gas turbine engine below a resonance speed of a starting spool of the gas turbine engine responsive to the regulated pressure.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 , wherein at least one valve of the compressed air source sets the regulated pressure.4. The system as in claim 3 , further comprising a controller that adjusts the at least one valve of the compressed air source in response to at least one parameter of the gas turbine engine to maintain the motoring speed of the gas turbine engine below the resonance speed.5. The system as in claim 4 , wherein the at least one parameter comprises one or more of: an engine speed of the gas turbine engine claim 4 , a starter speed of the air turbine starter claim 4 , and a ...

PNEUMATIC CONTROL VALVE

A control valve for a gas turbine engine air starter. The control valve includes a spherical or ball valve element rotatable between a closed position and an open position to connect an internal flow passage to the air starter. A series of camming elements interconnecting a piston and a valve stem for the spherical valve element convert linear displacement of the piston into rotational movement of the valve for rapid opening. 1. A control valve for fluid flow , said valve comprising:a valve body having an inlet and an aligned outlet passage, and an interconnecting chamber;a valve element positioned within said chamber and having a through flow passage, said valve element being rotatable about an axis between a first position in which the through flow passage aligns with and connects said inlet and outlet passages in said valve body and a second position in which said valve element blocks flow between said inlet and outlet passages;a stem extending from said valve body coaxial with said valve body axis;a chamber receiving said stem; anda piston displaceable within said chamber in a direction parallel to the axis of said stem, said chamber, piston and stem having inter engaging camming elements for connecting the linear displacement of said piston along said axis into rotation of said stem and valve body between said first and second positions.2. The control valve as claimed in claim 1 , wherein the valve element is spherical and the through flow passage extends through the axis of rotation of the valve element.3. The control valve as claimed in claim 2 , further comprising annular seats providing sealing surfaces between the valve body and the spherical valve element.4. The control valve as claimed in claim 1 , further comprising a source of pressurized control air and a valve selectively operable to apply pressurized air to said piston to displace it in a direction opening the valve body.5. The control valve as claimed in claim 4 , further comprising a spring ...

STARTER AIR VALVE SYSTEM WITH REGULATING BLEED

A system includes a starter air valve with a manual override and a pressure regulating bleed valve in fluid communication with the starter air valve. The starter air valve is 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 pressure regulating bleed valve is operable to bleed a portion of the compressed air flow to produce a bleed controlled starter air flow to limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to detection of the manual override in an open position. 1. A system comprising:a starter air valve comprising a manual override, the 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; anda pressure regulating bleed valve in fluid communication with the starter air valve, the pressure regulating bleed valve operable to bleed a portion of the compressed air flow to produce a bleed controlled starter air flow to limit a motoring speed of the gas turbine engine below a resonance speed of the gas turbine engine responsive to detection of the manual override in an open position.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 torque motor operable to open the pressure regulating bleed valve.4. The system as in claim 1 , further comprising a solenoid operable to open the pressure regulating bleed valve.5. The system as in claim 1 , further comprising a switch operable to detect the manual override in the open position.6. The system as in claim 1 , further comprising a sensor operable to detect the manual override in the open position.7. The system as in claim 1 , wherein the starter air valve and the pressure regulating ...

TURBOMACHINE TRAIN AND METHOD FOR COUPLING THE TURBOMACHINE TRAIN

A turbomachine train with two shaft parts which each have a fixedly attached grooved wheel, with a first overrunning clutch, with two rotational speed sensors and with a control device. The clutch is designed to couple and decouple the first shaft part to and from the second shaft part. The first rotational speed sensor measures the rotational speed of the first grooved wheel. The second rotational speed sensor measures the rotational speed of the second grooved wheel. The control device determines the differential angle between the first shaft part and the second shaft part and accelerates the turbomachines, with an acceleration value determined on the basis of the measured rotational speeds and on the basis of the differential angle, such that the two shaft parts couple together at a predetermined target coupling angle. 1. A turbomachine train , comprising:a first shaft section which has a first turbomachine and first slotted wheel which is fixedly attached on the first shaft section,a second shaft section which has a second turbomachine and second slotted wheel which is fixedly attached on the second shaft section,a first overrunning clutch which is designed for coupling the first shaft section to the second shaft section when the rotational speed of the first shaft section is equal to the rotational speed of the second shaft section, and for decoupling the first shaft section from the second shaft section when the rotational speed of the first shaft section is lower than the rotational speed of the second shaft section,a first tachometer which is designed for measuring the rotational speed of the first slotted wheel,a second tachometer which is designed for measuring the rotational speed of the second slotted wheel, anda control device which is adapted to determine the differential angle between the first shaft section and the second shaft section and, at a rotational speed of the second shaft section which is lower than a nominal rotational speed of the ...

DUAL MODE STARTER GENERATOR

A system for starting a turbine engine. The system may comprise a gearbox, a first starter, and a second starter. The gearbox may have a gearbox input shaft. The gearbox may be coupled to the turbine engine. The gearbox input shaft may be rotatively coupled to a spool of the turbine engine. The first starter may be coupled to the gearbox input shaft. The second starter may have a second-starter output shaft. The second-starter output shaft may be coaxial with the gearbox input shaft. The second starter may be coupled to the gearbox input shaft through the first starter. 1. A system for starting a turbine engine , comprising:a gearbox having a gearbox input shaft, said gearbox coupled to said turbine engine and said gearbox input shaft rotatively coupled to a spool of the turbine engine;a first starter coupled to said gearbox input shaft; anda second starter having a second-starter output shaft, said second-starter output shaft coaxial with the gearbox input shaft,wherein the second starter is coupled to gearbox input shaft through said first starter.2. The system of claim 1 , wherein the first starter is an air turbine starter and the second starter is an electric starter-generator claim 1 , the electric starter-generator being connected alternatively between an auxiliary power source and an auxiliary load.3. The system of claim 1 , wherein the first starter is an electric starter-generator and the second starter is an air turbine starter claim 1 , the electric starter-generator being connected alternatively between an auxiliary power source and an auxiliary load.4. The system of claim 3 , wherein said second starter is selectively coupleable to the first starter.5. The system of claim 4 , wherein said second starter is selectively coupleable to the first starter via a overrunning clutch.6. The system of claim 1 , further comprising a mounting member connecting either of said first starter and said second starter and a casing of said turbine engine.7. The system of ...

ACCESSORY GEARBOX WITH OPPOSITELY DISPOSED STARTER/GENERATOR AND AIR TURBINE STARTER

A system for starting a turbine engine is provided. The system may comprise an gearbox, and electric starter, and an air turbine starter. The gearbox may have a gearbox input shaft. The gearbox input shaft may be coupled to a turbine engine. The gearbox input shaft may be rotationally coupled to a spool of the turbine engine. The electric starter may be coupled to the gearbox input shaft. The air turbine starter may be coupled to the gearbox input shaft. The electric starter and the air turbine starter may be separated by the gearbox. The electric starter may be a starter-generator connected alternatively between an auxiliary power source and an auxiliary load. 1. A system for starting a turbine engine , comprising:a gearbox having a gearbox input shaft, said gearbox coupled to said turbine engine, the gearbox input shaft rotationally coupled to a spool of the turbine engine;an electric starter coupled to said gearbox input shaft; andan air turbine starter coupled to said gearbox input shaft,wherein said electric starter and said air turbine starter are separated by the gearbox and the electric starter is a starter-generator connected alternatively between an auxiliary power source and an auxiliary load.2. The system of claim 1 , wherein said air turbine starter comprises a shaft coaxial with said gearbox input shaft.3. The system of claim 2 , wherein said electric starter comprises a shaft coaxial with said gearbox input shaft.4. The system of claim 1 , wherein both of said electric starter air turbine starters comprise an output shaft claim 1 , wherein said output shaft is said gearbox input shaft.5. The system of claim 1 , further comprising a second gearbox coupling said electric starter and said gearbox input shaft.6. The system of claim 5 , wherein said electric starter is coupled to said gearbox input shaft via a lay shaft and said second gearbox claim 5 , the second gear box having an input to output ratio less than 1.7. The system of claim 1 , further ...

Air turbine starter with decoupler

A method and decoupler for disengaging an output member from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a shaft and a retention mechanism selectively coupling the output member to the shaft. In a backdrive event, the decoupler decouples the member from a drive shaft.

Autothrottle control system on turbopropeller-powered aircraft

Herein provided are methods and systems for a method for controlling autothrottle of an engine. A digital power request is obtained from an autothrottle controller, the digital power request based on an autothrottle input to the autothrottle controller. A manual input mode for the engine is terminated, the manual input mode based on a second power request obtained from a manual input associated with the engine. An autothrottle mode for the engine is engaged to control the engine based on the digital power request.

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 ...

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 SUPPLYING COMPRESSED AIR TO A MAIN ENGINE STARTER MOTOR

A system and method for supplying compressed air from an auxiliary power unit to a main engine starter motor. The inlet guide vanes are controlled using either first or second inlet guide vane control logic and the surge control valve is controlled using either first or second surge control valve control logic. When the first inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand signal, when the second inlet guide vane control logic is used, the inlet guide vanes are positioned based on a demand schedule, when the first surge control valve logic is used, the surge control valve can be commanded to repeatedly move to only a fully-closed position and a fully-open position, and when the second surge control valve logic is used, the surge control valve can be commanded to the fully-closed position only when maximum flow is commanded. 1. A system for supplying compressed air to a main engine starter motor , comprising:an auxiliary power unit (APU) including a compressor section and a turbine section, the compressor section including adjustable inlet guide vanes that are moveable to a plurality of inlet guide vane positions;a main engine start conduit coupled to receive compressed air from the compressor section and supply the compressed air to the main engine starter motor;a surge control valve in fluid communication with the main engine start conduit, the surge control valve responsive to valve position commands to move between a fully-closed position and a plurality of open positions between the fully-closed and a fully-open position; andan APU control unit in operable communication with the APU and the surge control valve and configured to control the APU, the inlet guide vanes, and the surge control valve, the APU control unit configured to selectively control at least the inlet guide vanes and surge control valve using first or second inlet guide vane control logic and first or second surge control valve control logic, ...

Air starter with bearing cooling

An air starter for starting a turbine engine that includes a housing, a turbine, an output shaft, and at least one bearing. The housing can define an interior where the turbine couples to the output shaft. A primary air flow path extends through the housing where air from the turbine can be exhausted through a primary outlet or a cooling outlet.

AIR TURBINE STARTER AIR VALVE

A starter air valve has a valve member and an actuator. A rotary spool valve has a rotatable valve body and an outer housing to selectively provide three modes of operation for the starter air valve. A first mode of operation connects air through the rotatable valve body to communicate with an actuator control, and to receive air back from the actuator control. The rotatable valve body then communicates the air to the actuator. In a second mode the rotatable valve body blocks communication between the actuator control and the actuator, and delivers air through a variable area port in a wall of the rotatable valve body to bypass the valve member. In a third mode the rotatable valve body blocks communication between the actuator and the actuator control, and connects air to the actuator without having passed to the actuator control. A starter air system is also disclosed. 1. A starter air valve for an air turbine starter system comprising:a valve member and an actuator for said valve member;a rotary spool valve to be connected to a source of pressurized air, said rotary spool valve having a rotatable valve body and an outer housing;an actuator control for said actuator;said rotatable valve body and said valve housing selectively providing three modes of operation for the starter air valve;in a first mode of operation the rotatable valve body connects pressurized air through said rotatable valve body to communicate with said actuator control, and receives pressurized air back from said actuator control, and then communicates the air to said actuator;in a second mode the rotatable valve body blocks communication between said actuator control and said actuator, and delivers air through a variable area port in an outer wall of said rotatable valve body to bypass said valve member; andin a third mode the rotatable valve body blocks communication between said actuator and said actuator control, and connects pressurized air to said actuator without having passed to said ...

Starter Motor Shared Lubrication System

A starter motor has a housing. The housing receives the starter motor and a plurality of locations to receive lubricant. The lubricant supply system shares a lubricant source with a main gas turbine engine to be started by the starter motor. The lubricant supply system has a shutoff valve. The shutoff valve is opened when starter motor is being driven to start a main gas turbine engine. The shutoff valve is generally closed once the main gas turbine engine is started.

STARTER ISSUE DETECTION

Systems and methods for detecting an issue with a starter are provided. One example aspect of the present disclosure is directed to a method for detecting an anomaly with an air turbine starter. The method includes receiving, by one or more controllers, data indicative of a frequency associated with an integrated air turbine starter from one or more sensors located on a stationary portion of the air turbine starter to monitor a rotating portion of the air turbine starter. The method includes determining, by the one or more controllers, an anomaly associated with the integrated air turbine starter based at least in part on the data indicative of the frequency. The method includes providing, by the one or more controllers, a notification indicative of the anomaly associated with the integrated air turbine starter. 1. A method for detecting an anomaly with an air turbine starter , the method comprising:receiving, by one or more controllers, data indicative of a frequency associated with an integrated air turbine starter from one or more sensors located on a stationary portion of the air turbine starter to monitor a rotating portion of the air turbine starter;determining, by the one or more controllers, an anomaly associated with the integrated air turbine starter based at least in part on the data indicative of the frequency; andproviding, by the one or more controllers, a notification indicative of the anomaly associated with the integrated air turbine starter.2. The method of claim 1 , wherein the anomaly associated with the integrated air turbine starter indicates an anomaly with the engine.3. The method of claim 1 , wherein the anomaly associated with the integrated air turbine starter indicates an anomaly with the accessory gearbox..4. The method of claim 1 , wherein at least one of the one or more starter sensors is an accelerometer.5. The method of claim 1 , wherein at least one of the one or more starter sensors is a microphone.6. The method of claim 1 , ...

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.

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.

AIR TURBINE STARTER WITH DECOUPLER

A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a an output shaft, drive shaft, and a retention mechanism selectively coupling the output shaft to the drive shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft. 1. A decoupler assembly for decoupling an output shaft of a starter motor during backdrive , comprising:a fuse having a first end operably coupled to a drive shaft of the starter motor, a threaded portion receivable within an internal threaded portion of the output shaft of the starter motor, and a neck portion located between the first end and the threaded portion; wherein when the threaded portion of the fuse is unwound from the internal threaded portion in a direction away from the drive shaft.2. The decoupler of claim 1 , wherein the tensile fuse shears at the neck portion when the threaded portion of the tensile fuse is unwound from the internal threaded portion.3. The decoupler of claim 2 , further comprising a thread insert operably coupled to the drive shaft and having a threaded portion that receives a threaded portion of the output shaft of the starter motor.4. The decoupler of claim 3 , wherein the tensile fuse is threaded into the output shaft with an opposite hand turn to the threads between the output shaft and the thread insert.5. The decoupler of claim 4 , wherein when the overrunning torque reaches the certain level the output shaft is unthreaded from the thread insert such that the output shaft is uncoupled from the drive shaft when the tensile fuse is unwound from the output shaft.6. The decoupler of claim 5 , further comprising a blocking mechanism movable between an expanded position and a retracted position and configured to bar the output shaft from rethreading with the thread insert when in the retracted position.7. The decoupler of claim 1 , wherein when a driving torque is transmitted from the ...

TURBOMACHINE AIR STARTER COMPRISING FIRST AND SECOND LUBRICATION COMPARTMENTS

A turbomachine air starter, including a first compartment wherein non-overrunning elements of the air starter are situated, corresponding to elements which are only run in the turbomachine starting phase, and a second compartment wherein overrunning elements of the air starter are situated, corresponding to the elements which are run throughout an operating time of the turbomachine, including the starting phase. The first compartment includes an oil receptacle for oil splash lubrication of the non-overrunning elements, and the second compartment includes an AWC type oil cavity for lubrication of the overrunning elements supplied by the lubrication oil return of the overrunning elements, in turn supplied with pressurized lubrication oil supplied by the turbomachine, the receptacle and the cavity being internal to the air starter. 110-. (canceled)11: A turbomachine air starter comprising:a first compartment wherein non-overrunning elements of the air starter are situated, corresponding to elements which are only run in a turbomachine starting phase;a second compartment wherein overrunning elements of the air starter are situated, corresponding to the elements which are run throughout an operating time of the turbomachine, including the starting phase;the first compartment comprising an oil receptacle for oil splash lubrication of the non-overrunning elements, and the second compartment comprising an AWC type oil cavity for lubrication of the overrunning elements supplied by the lubrication oil return of the overrunning elements, in turn supplied with pressurized lubrication oil supplied by the turbomachine, the receptacle and the cavity being internal to the air starter.12: An air starter according to claim 11 , wherein the oil receptacle for oil splash lubrication of the first compartment communicates with the AWC type oil cavity of the second compartment via a first opening enabling equilibration of oil levels between the receptacle and the cavity.13: An air starter ...

AIR TURBINE STARTER WITH LUBRICATION VALVE

An air turbine starter includes a transfer tube having a lubrication inlet and a lubrication outlet configured to allow fluid to flow therethrough. A valve is positioned within the transfer tube including a spring. The spring is configured to selectively allow fluid flow within the transfer tube based on fluid pressure differential across the valve. The spring can have three positions: a first position configured to prevent flow within the transfer tube, an intermediate position configured to allow free flow of fluid within the transfer tube, and a compressed positioned to prevent flow to the lubrication outlet. 1. An Air Turbine Starter (ATS) , comprising:a transfer tube having a lubrication inlet and a lubrication outlet configured to allow fluid to flow therethrough; anda valve positioned within the transfer tube including a spring, wherein the spring is configured to selectively allow fluid flow within the transfer tube based on fluid pressure differential across the valve.2. The ATS of claim 1 , wherein the spring has three positions: a first position configured to prevent flow within the transfer tube claim 1 , an intermediate position configured to allow free flow of fluid within the transfer tube claim 1 , and a compressed positioned to prevent flow to the lubrication outlet.3. The ATS of claim 2 , wherein the spring is in the first position when zero pressure differential is measured across the valve.4. The ATS of claim 3 , wherein the spring is in the intermediate position when an intermediate pressure differential is measured across the valve claim 3 , the intermediate pressure being greater than zero pressure and less than a flight pressure.5. The ATS of claim 4 , wherein the spring is in the compressed position when a flight pressure differential is measured across the valve claim 4 , the flight pressure being greater than an intermediate pressure.6. The ATS of claim 1 , further comprising a first set of radial holes positioned proximate the lubrication ...

GAS TURBINE ENGINE DUAL TOWERSHAFT ACCESSORY GEARBOX ASSEMBLY WITH A TRANSMISSION

A gas turbine engine assembly includes a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure, first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted, first and second towershafts respectively coupled to the first and second turbine shafts, an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train, a hydraulic pump, a transmission coupling the hydraulic pump to the first gear train, the transmission transitionable between a first mode where the hydraulic pump is driven at a first speed relative to the first towershaft, a second mode where the hydraulic pump is driven at a different, second speed relative to the first towershaft, and a third mode where the hydraulic pump is driven at a different, third speed relative to the first towershaft. 1. A gas turbine engine assembly comprising:a turbine section having first and second turbines mounted for rotation about a common rotational axis within an engine static structure;first and second turbine shafts coaxial with one another and to which the first and second turbines are respectively operatively mounted;first and second towershafts respectively coupled to the first and second turbine shafts;an accessory drive gearbox mounted to the engine static structure, the accessory drive gearbox including a first gear train and a second gear train, the first towershaft extending into a housing and coupled to the first gear train, the second towershaft extending into the housing and coupled to the second gear train;a hydraulic pump; anda transmission coupling the hydraulic pump to the first gear train, the ...

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 ...

DEVICE AND METHOD FOR TESTING THE INTEGRITY OF A HELICOPTER TURBINE ENGINE RAPID RESTART SYSTEM

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter includes a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurised air from the turboshaft engine; a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas The device further includes a sensor for determining the rotational speed of the pneumatic turbine. 1. A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter , comprising a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with pressurised gas , upon a command , by a pneumatic supply circuit such that it is possible to rotate said turboshaft engine and ensure that the turboshaft engine is reactivated , said testing device comprising:an apparatus configured to withdraw pressurised air from the turboshaft engine;a duct configured to convey said withdrawn air to said pneumatic circuit for supplying said pneumatic turbine; anda sensor configured to determine the rotational speed of said pneumatic turbine.2. The device according to claim 1 , further comprising an electrovalve arranged in the region of a joining point between the pneumatic circuit and said air-conveying duct claim 1 , said electrovalve being configured to open an air passage between said air-conveying duct and said pneumatic circuit upon a command from a control unit and in the absence of a pressurised gas supply from said pneumatic circuit claim 1 , and to close said air passage in the absence of a command or in the presence of a pressurised gas supply from said pneumatic circuit.3. The device according to claim 2 , wherein said electrovalve comprises a preloaded ...

SYSTEM AND METHOD FOR EMERGENCY STARTING OF AN AIRCRAFT TURBOMACHINE

The invention relates to an emergency start system () for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (), an electrically controlled ignition device (), a computer () connected to the ignition device, and at least one starter motor () comprising a turbine () for driving a shaft () intended for being coupled to a shaft () of the turbine engine, the outlet of the gases from the generator being connected to the inlet () of the turbine of the starter motor. 1. Emergency start system for turbine engines of an aircraft , characterised in that it comprises at least one solid-propellant gas generator , an electrically controlled ignition device , a computer connected to the ignition device , and at least two independent starter motors , each intended for starting one turbine engine , each starter motor comprising a turbine for driving a shaft intended for being coupled to a shaft of the corresponding turbine engine , the outlet of the gases from the generator being connected to the inlet of the turbine of each starter motor by means of the same distribution valve connected to the computer.2. System according to claim 1 , characterised in that the output of the turbine of each starter motor is connected to the exhaust.3. System according to claim 1 , characterised in that the turbine of each starter motor comprises a single rotor wheel.4. System according to claim 1 , characterised in that it comprises means for coupling the shaft driven by the turbine to the shaft of the turbine engine claim 1 , said coupling means comprising a freewheel designed to transmit a driving torque only when said torque comes from the starter motor.5. Aircraft comprising at least two turbine engines claim 1 , characterised in that it comprises an emergency start system according to .6. Method for emergency starting a turbine engine of an aircraft by means of a system according to claim 1 , characterised in that the ignition device ...

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 ...

ELECTRO-PNEUMATIC GAS TURBINE ENGINE MOTORING SYSTEM FOR BOWED ROTOR ENGINE STARTS

A system for cooling a gas turbine engine is provided, the system comprising: a gas turbine engine including rotational components comprising an engine compressor, an engine turbine, and a rotor shaft operably connecting the engine turbine to the engine compressor, wherein each rotational component is configured to rotate when any one of the rotational components is rotated; an electro-pneumatic starter operably connected to at least one of the rotational components, the electro-pneumatic starter being configured to rotate the rotational components; an electric drive motor operably connected to the electro-pneumatic starter, the electric drive motor being configured to rotate the rotational components through the electro-pneumatic starter; and a motor controller in electronic communication with the electric drive motor, the motor controller being configured to command the electric drive motor to rotate the rotational components at a selected angular velocity for a selected period of time. 1. A system for cooling a gas turbine engine , the system comprising:a gas turbine engine including rotational components comprising an engine compressor, an engine turbine, and a rotor shaft operably connecting the engine turbine to the engine compressor, wherein each rotational component is configured to rotate when any one of the rotational components is rotated;an electro-pneumatic starter operably connected to at least one of the rotational components, the electro-pneumatic starter being configured to rotate the rotational components;an electric drive motor operably connected to the electro-pneumatic starter, the electric drive motor being configured to rotate the rotational components through the electro-pneumatic starter; anda motor controller in electronic communication with the electric drive motor, the motor controller being configured to command the electric drive motor to rotate the rotational components at a selected angular velocity for a selected period of time.2. ...

DRIVE ASSEMBLY FOR A GAS TURBINE ENGINE

A drive assembly for a gas turbine engine according to an exemplary embodiment includes, among other things, an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, and at least one engagement feature on a component of the gear train. An actuator is engageable with the at least one engagement feature to cause the accessory drive shaft to rotate. A method of driving a section of a gas turbine engine is also disclosed. 1. A drive assembly for a gas turbine engine comprising:an epicyclic gear train having an input and an output, the input coupled to a first turbine, the output coupled to an accessory drive shaft, wherein the gear train includes a plurality of components including a sun gear, a ring gear, a plurality of star gears meshing with the sun gear and the ring gear, and a carrier, and wherein the gear train includes at least one engagement feature on one of the plurality of components; andan actuator engageable with the at least one engagement feature to cause the accessory drive shaft to rotate.2. The drive assembly as recited in claim 1 , comprising a housing defining a cavity claim 1 , the first turbine claim 1 , the gear train and the actuator located at least partially in the cavity.3. The drive assembly as recited in claim 1 , wherein the epicyclic gear train is a star gear system claim 1 , the input of the gear train is defined by the sun gear claim 1 , and the output of the gear train is defined by the ring gear such that the gear train interconnects the first turbine and the accessory drive shaft.4. The drive assembly as recited in claim 3 , wherein the ring gear defines the at least one engagement feature.5. The drive assembly as recited in claim 4 , wherein the at least one engagement feature defines one or more protrusions circumferentially arranged about and extending outwardly from a perimeter of the ring gear.6. The drive assembly as recited in claim 1 , wherein ...

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 ...

CABIN BLOWER SYSTEM

An aircraft cabin blower system is described having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device. The first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine. The first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump. When, in use, the system is operating in a cabin blower configuration, a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device, which in turn rotates the cabin blower compressor. 1. An aircraft cabin blower system having a hydraulic circuit comprising a first hydraulic device and a second hydraulic device , wherein the first hydraulic device is mechanically coupled to a cabin blower compressor and the second hydraulic device is arranged in use to be mechanically coupled to a spool of a gas turbine engine and where further the first hydraulic device is capable of performing as a hydraulic motor and the second hydraulic device is capable of performing as a hydraulic pump , such that when , in use , the system is operating in a cabin blower configuration , a driving force supplied by the spool of the gas turbine causes the second hydraulic device to pump liquid provided in the hydraulic circuit and thereby to drive the first hydraulic device , which in turn rotates the cabin blower compressor.2. An aircraft cabin blower system according to where the first hydraulic device is capable of performing as a hydraulic pump and the second hydraulic device is capable of performing as a hydraulic motor such that when claim 1 , in use claim 1 , the system is operating in an engine start configuration claim 1 , a driving force supplied by the cabin blower compressor acting as ...

BOWED ROTOR START USING A VARIABLE POSITION STARTER VALVE

A bowed rotor start mitigation system for a gas turbine engine is provided. The bowed rotor start mitigation system includes a variable position starter valve and a controller. The controller is operable to dynamically adjust the variable position starter valve to deliver a starter air supply to a starter to drive rotation of a starting spool of the gas turbine engine according to a dry motoring profile that continuously varies a rotor speed of the starting spool up to a point below a critical rotor speed. 1. A bowed rotor start mitigation system for a gas turbine engine , the bowed rotor start mitigation system comprising:a variable position starter valve; anda controller operable to dynamically adjust the variable position starter valve to deliver a starter air supply to a starter to drive rotation of a starting spool of the gas turbine engine according to a dry motoring profile that continuously varies a rotor speed of the starting spool up to a point below a critical rotor speed.2. The bowed rotor start mitigation system as in claim 1 , wherein the dry motoring profile is essentially increasing continuously.3. The bowed rotor start mitigation system as in claim 1 , wherein the controller monitors the rotor speed and dynamically adjusts a valve angle of the variable position starter valve to maintain the rotor speed along a target rotor speed profile defined in the dry motoring profile.4. The bowed rotor start mitigation system as in claim 3 , wherein the target rotor speed profile extends above the critical rotor speed and the controller dynamically adjusts the valve angle of the variable position starter valve to maintain the rotor speed along the target rotor speed profile across the critical rotor speed up to an engine idle speed.5. The bowed rotor start mitigation system as in claim 3 , wherein a slope of the target rotor speed profile in the dry motoring profile is adjusted and maintains a positive slope while bowed rotor start mitigation is active based on ...

GAS TURBINE ENGINE MOTORING VARIABLE FREQUENCY GENERATOR SYSTEM FOR BOWED ROTOR ENGINE STARTS

An engine starting system for a gas turbine engine is provided. The engine starting system comprising: a gas turbine engine including rotational components comprising an engine compressor, an engine turbine, and a rotor shaft operably connecting the engine turbine to the engine compressor, wherein each rotational component is configured to rotate when any one of the rotational components is rotated; a variable frequency generator operably connected to at least one of the rotational components, the variable frequency generator being configured to rotate the rotational components; and a motor controller in electronic communication with the variable frequency generator, the motor controller being configured to command the variable frequency generator to rotate the rotational components at a selected angular velocity for a selected period of time. 1. An engine starting system for a gas turbine engine comprising:a gas turbine engine including rotational components comprising an engine compressor, an engine turbine, and a rotor shaft operably connecting the engine turbine to the engine compressor, wherein each rotational component is configured to rotate when any one of the rotational components is rotated;a variable frequency generator operably connected to at least one of the rotational components, the variable frequency generator being configured to rotate the rotational components; anda motor controller in electronic communication with the variable frequency generator, the motor controller being configured to command the variable frequency generator to rotate the rotational components at a selected angular velocity for a selected period of time.2. The engine starting system of claim 1 , further comprising:an accessory gearbox operably connecting the variable frequency generator to at least one of the rotational components.3. The engine starting system of claim 1 , wherein:the variable frequency generator is configured to generate electricity when the rotational ...

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 ...

Removable Pack for Reactivating a Turboshaft Engine, Architecture for a Multi-Engine System for Propelling a Helicopter, provided with such a Pack, and Corresponding Helicopter

The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine () being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator. 1. A removable pack for the reactivation of a turboshaft engine of a helicopter , comprising a gas generator equipped with a drive shaft , said turboshaft engine being capable of operating in at least one standby mode during a stable flight of the helicopter , said removable pack comprising:a removable gearbox comprising a gearbox output shaft, [{'b': '34', 'a first reactivation device that is mounted on said gearbox and comprises a shaft that is referred to as the first gearbox input shaft () and is mechanically connected to said gearbox output shaft, and controlled means for rotating said first gearbox input shaft,'}, 'a second reactivation device that is mounted on said gearbox and comprises a shaft that is referred to as the second gearbox input shaft and is mechanically connected to said output shaft, and controlled means for rotating said second gearbox input shaft,, 'controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine, comprising at leastmechanical means capable of reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.2. The pack according to claim 1 , wherein said means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator are formed by an accessory gearbox of said turboshaft engine.3. The pack according to claim 1 , wherein said controlled ...

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 ...

Alternating starter use during multi-engine motoring

A system is provided for alternating starter use during multi-engine motoring in an aircraft. The system includes a first engine starting system of a first engine. A first controller is in communication with a second controller that controls a second engine starting system of a second engine, the first controller being configured to intermittently direct power to the first engine starting system to alternately accelerate and decelerate the first engine during motoring with respect to the second engine.

AIR TURBINE STARTER CONTAINMENT SYSTEM

An air turbine starter for starting an engine, comprising a housing having an interior surface defining an interior, at least one turbine member rotatably mounted within the interior about a rotational axis, and having a plurality of circumferentially spaced blades, and a containment structure radially overlying and circumferentially surrounding the at least one turbine member extending between an outer surface and an inner surface to define a radial direction.

MODIFIED START SEQUENCE OF A GAS TURBINE ENGINE

A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (f), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Nthat is less than a speed to start the gas turbine engine, where tis a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of Nto Nfor homogenizing engine temperatures. 1. A gas turbine engine and a system for controlling a start sequence of the gas turbine engine , comprising:an electronic engine control system;a thermal model resident upon the electronic engine control system and configured to synthesize a heat state of the gas turbine engine;a memory for recording the current heat state of the gas turbine engine at shutdown and for recording a shutdown time of the gas turbine engine;{'sub': motoring', 'target', 'motoring, 'a model for determining a time period (t) for motoring the gas turbine engine at a predetermined speed Nwherein the predetermined speed is less than a speed used to start the gas turbine engine and wherein tis a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time; and'}{'sub': targetMin', 'targetMax, 'a controller for modulating a starter valve of a starter of the gas turbine engine in order to maintain the gas turbine engine within a predetermined speed range of Nto Nfor homogenizing engine temperatures.'}2. The gas turbine engine and system of claim 1 , wherein the time period (t) is calculated ...

AIR TURBINE STARTER WITH AUTOMATED VARIABLE INLET VANES

According to one embodiment, an air turbine starter is provided. The air turbine starter comprising: a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub; an inlet housing at least partially surrounding the turbine wheel; a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades; and a plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing; wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane. 1. An air turbine starter comprising:a turbine wheel including a hub integrally attached to a turbine rotor shaft and a plurality of turbine blades extending radially outward from the hub;an inlet housing at least partially surrounding the turbine wheel;a nozzle located upstream from the turbine wheel and contained within the inlet housing defining an inlet flowpath between the nozzle and the inlet housing, the inlet flowpath directs air flow into the turbine blades; anda plurality of turbine vanes rotatably connected to the nozzle, each turbine vane extending radially from the nozzle into the inlet flowpath towards the inlet housing;wherein the plurality of turbine vanes are operable to adjust air flow through the inlet flowpath by rotating each turbine vane.2. The air turbine starter of claim 1 , further comprising:at least one actuator operably connected to at least one turbine vane, the at least one actuator in operation rotates at least one turbine vane.3. The air turbine starter of claim 2 , wherein:the at least one actuator is at least one of a pneumatic actuator, an electric actuator, and a hydraulic actuator.4. The air turbine starter ...

Method and system for starting up an aircraft turbomachine by real-time regulation of air flow

The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

AIR TURBINE STARTER SYSTEMS INCLUDING GEARBOX-INTEGRATED CLUTCH MODULES AND GAS TURBINE ENGINES EMPLOYING THE SAME

Air Turbine Starter (ATS) systems are provided, as gas turbine engines including ATS systems. In one embodiment, a gas turbine engine includes an accessory gearbox (AGB) and an integrated Air Turbine Starter (ATS) system. The AGB includes a gearbox gear train within a gearbox housing. The integrated ATS system is removably installed on the AGB and includes an ATS having an air turbine and an output shaft coupled thereto. An ATS clutch module is coupled to the ATS output shaft. The ATS clutch module is further within the gearbox housing and mechanically couples the ATS output shaft to the gearbox gear train when the integrated ATS system is installed on the AGB. 1. A gas turbine engine , comprising: a gearbox housing; and', 'a gearbox gear train within the gearbox housing; and, 'an accessory gearbox (AGB), comprising an ATS including an air turbine and an ATS output shaft coupled thereto; and', 'an ATS clutch module coupled to the ATS output shaft, the ATS clutch module received within the gearbox housing and mechanically coupling the ATS output shaft to the gearbox gear train when the integrated ATS system is installed on the AGB., 'an integrated Air Turbine Starter (ATS) system removably installed on the AGB, the integrated ATS system comprising2. The gas turbine engine of wherein the ATS clutch module comprises:a first race formed on a mating end portion of the ATS output shaft;a second race co-axial with the first race; anda plurality of unidirectional clutch elements captured between the first and second races.3. The gas turbine engine of wherein the ATS clutch module further comprises a splined ring on which the second race is formed.4. The gas turbine engine of wherein the gearbox gear train comprises:an input gear; anda splined interface coupled to the input gear and engaging the splined ring to provide a rotationally fixed coupling when the integrated ATS is installed on the AGB.5. The gas turbine engine of wherein the input gear has a central opening into ...

DUAL REDUNDANT TWO-STAGE VALVE

A vehicle power generation system including: a first solenoid spool valve; a second solenoid spool valve; a first poppet valve fluidly connected to a high pressure inlet; a second poppet valve fluidly connected to the first solenoid spool valve and the first poppet valve; a third poppet valve fluidly connected to the second solenoid spool valve, the first poppet valve, and an impulse turbine; and a fourth poppet valve fluidly connected to the second solenoid spool valve, the second poppet valve, and the impulse turbine. 1. A vehicle power generation system comprising:a first solenoid spool valve;a second solenoid spool valve;a first poppet valve fluidly connected to a high pressure inlet;a second poppet valve fluidly connected to the first solenoid spool valve and the first poppet valve;a third poppet valve fluidly connected to the second solenoid spool valve, the first poppet valve, and an impulse turbine; anda fourth poppet valve fluidly connected to the second solenoid spool valve, the second poppet valve, and the impulse turbine.2. The vehicle power generation system of claim 1 , wherein the first solenoid spool valve further comprises:a spool housing;a spool located at least partially within the spool housing, the spool fluidly separating the spool housing into a first spool housing chamber, a second spool housing chamber, a third spool housing chamber, and a fourth spool housing chamber; anda solenoid operably connected to the spool, the solenoid being configured to translate the spool linearly within the spool housing.3. The vehicle power generation system of claim 2 , wherein the fourth spool housing chamber is located proximate the solenoid and the first spool housing chamber is located opposite the fourth spool housing chamber claim 2 , wherein the second spool housing chamber and the third spool housing chamber are linearly interposed between the first spool housing chamber and the fourth spool housing chamber claim 2 , and wherein the second spool ...

PROGNOSTIC MONITORING AND FAILURE DETECTION OF ROTATING COMPONENTS

A method of monitoring a rotating component includes gathering an electrical signal from a sensor arranged adjacent a rotating component of an assembly. The electrical signal is transformed from a time domain into a frequency domain. The electrical signal is compared to an expected signal. 1. A method of monitoring a rotating component , comprising:gathering an electrical signal from a sensor arranged adjacent a rotating component of an assembly;transforming the electrical signal from a time domain into a frequency domain; andcomparing the electrical signal to an expected signal.2. The method of claim 1 , comprising determining whether there is a fault in the assembly based on the comparison to the expected signal.3. The method of claim 2 , comprising determining a portion of the assembly containing the fault based on the comparison to the expected signal.4. The method of claim 2 , comprising determining whether the fault corresponds to an issue with a gear system claim 2 , shaft claim 2 , or bearing.5. The method of claim 2 , comprising replacing or repairing a component of the assembly when a fault is detected.6. The method of claim 1 , wherein the comparing step comprises comparing an amplitude of the electrical signal across several frequencies with the expected signal.7. The method of claim 1 , comprising removing any high amplitude pulses from the electrical signal before the transforming step.8. The method of claim 1 , wherein the rotating component is a gear having at least one tooth.9. The method of claim 7 , wherein the high amplitude pulses corresponds to at least one tooth passing the sensor.10. The method of claim 7 , wherein the gear has a plurality of teeth spaced about a circumference of the gear.11. The method of claim 1 , wherein the assembly is an air turbine starter.12. The method of claim 1 , wherein the gathering step comprises gathering data at a frequency of at least twice a top rotating frequency of the rotating component.13. The method of ...

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 ...

DUAL-USE AIR TURBINE SYSTEM FOR A GAS TURBINE ENGINE

A dual-use air turbine system for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set. The dual-use air turbine system also includes a plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation. The valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation. 1. A dual-use air turbine system for a gas turbine engine of an aircraft , the dual-use air turbine system comprising:a variable area air turbine mechanically linked to a spool of the gas turbine engine through a multi-speed gear set; anda plurality of valves in pneumatic ducting operable to direct an engine start air flow through an inlet of the variable area air turbine and drive rotation of the spool during an engine start mode of operation, wherein the valves are further operable to direct an engine bleed air flow from a compressor section of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.2. The dual-use air turbine system as in claim 1 , wherein the valves comprise a first check valve and a high pressure shutoff valve claim 1 , and the engine bleed air flow is provided from a lower pressure tap of the compressor section by the first check valve or a higher pressure tap of the compressor section by the high pressure shut-off valve.3. The dual-use air turbine system as in claim 2 , wherein the first check valve is opened during a high power condition of the gas turbine engine and the high ...

HYBRID AIRCRAFT TURBINE ENGINE STARTING SYSTEM AND METHOD

A system and method for starting an aircraft turbine engine includes a primary starting subsystem and a secondary starting subsystem. The primary starting subsystem is coupled to a shaft of the aircraft turbine engine and has a dedicated power source. The secondary starting subsystem is also coupled to the shaft of the aircraft turbine engine and has a shared power source. A controller controls the operation of the primary starting subsystem and the secondary starting subsystem while starting the aircraft turbine engine. The primary starting subsystem may be an Auxiliary Power Unit coupled to an Air Turbine Starter. The secondary starting subsystem may be a Starter Generator coupled to a battery also used to power the Emergency Hydraulic System. The primary starting subsystem is always operated at full power during starting while the secondary starting subsystem is preferably operated in a sequence of different power levels. 1. A system for starting an aircraft turbine engine , comprising:a primary starting subsystem coupled to a shaft of the aircraft turbine engine, the primary starting subsystem having a dedicated power source;a secondary starting subsystem coupled to the shaft of the aircraft turbine engine, the secondary starting subsystem having a shared power source; anda controller for controlling operation of the primary starting subsystem and the secondary starting subsystem while starting the aircraft turbine engine.2. The system of claim 1 , wherein the primary starting subsystem comprises an auxiliary power unit coupled to an air turbine starter.3. The system of claim 2 , wherein the auxiliary power unit comprises the dedicated power source.4. The system of claim 3 , wherein the auxiliary power unit has a total output capacity that is less than a total amount of power required to start the aircraft turbine engine.5. The system of claim 1 , wherein the primary starting subsystem comprises an integrated power unit coupled to a starter generator.6. The ...

MODIFIED START SEQUENCE OF A GAS TURBINE ENGINE

A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation. 1. A system for starting a gas turbine engine of an aircraft , the system comprising:a pneumatic starter motor;a discrete starter valve switchable between an on-state and an off-state; anda controller operable to perform a starting sequence for the gas turbine engine, the starting sequence comprising alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, wherein the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.2. The system as in claim 1 , wherein the electromechanical device has a cycle time defined between an off-command to an on-command to the off-command that is at most half of a movement time for the discrete starter valve to transition from fully closed to fully open.3. The system as in claim 1 , wherein the electromechanical device is a solenoid that positions the discrete starter valve based on intermittently supplied electric power.4. The system as in claim 1 , wherein the electromechanical device is an ...

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 end coupled to the output shaft and a second end; and', 'a magnetic coupling selectively linking the second end of the connector to the drive shaft, when driving torque is transmitted the connector is magnetically linked to 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, comprising2. The air turbine starter of wherein the ...

Method and System for Efficient Nonsynchronous LNG Production using Large Scale Multi-Shaft Gas Turbines

A drive system for liquefied natural gas (LNG) refrigeration compressors in a LNG liquefaction plant. Each of three refrigeration compression strings include refrigeration compressors and a multi-shaft gas turbine capable of non-synchronous operation. The multi-shaft gas turbine is operationally connected to the refrigeration compressors and is configured to drive the one or more refrigeration compressors. The multi-shaft gas turbine uses its inherent speed turndown range to start the one or more refrigeration compressors from rest, bring the one or more refrigeration compressors up to an operating rotational speed, and adjust compressor operating points to maximize efficiency of the one or more refrigeration compressors, without assistance from electrical motors with drive-through capability and variable frequency drives. 1. A drive system for liquefied natural gas (LNG) refrigeration compressors in a LNG liquefaction plant , comprising: one or more refrigeration compressors, and', start the one or more refrigeration compressors from rest,', 'bring the one or more refrigeration compressors up to an operating rotational speed, and', 'adjust compressor operating points to maximize efficiency of the one or more refrigeration compressors,', 'without assistance from electrical motors with drive-through capability and variable frequency drives;, 'a multi-shaft gas turbine capable of non-synchronous operation, the multi-shaft gas turbine being operationally connected to the one or more refrigeration compressors and configured to drive the one or more refrigeration compressors, wherein the multi-shaft gas turbine uses its inherent speed turndown range to'}], 'first, second, and third refrigeration compression strings, each refrigeration compression string including'}wherein the first refrigeration compression string is configured to provide compression to a propane refrigerant, the second refrigeration compression string is configured to provide compression to a mixed ...

AIR TURBINE STARTER WITH DECOUPLER

A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes an output shaft, drive shaft wherein the output shaft is selectively coupled to the drive shaft. Permanent magnets are used to transmit torque from the drive shaft to the output shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft by uncoupling the torque transfer.

SYNCHRONOUS ENGAGEMENT CLUTCH

A clutch assembly includes an output shaft extending along an axis and output teeth. A movable component is disposed adjacent to the output component. The movable component includes drive teeth and an annular engagement weight track including a groove circumscribing the axis. The movable component is movable between an engaged position, wherein the drive teeth are drivingly engaged with the output teeth, and a disengaged position, wherein the drive teeth are not engaged with the output teeth. An input component is disposed adjacent to the movable component. The input component includes engagement weight pockets. Spherical engagement weights are disposed in each engagement weight pocket. The groove has a generally uniform radial cross section across its circumference.

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. 1. An air turbine starter for 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 and having a turbine output shaft;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 where the sun gear is coupled to the turbine output shaft; anda drive shaft configured to be operably coupled to and rotate with the engine;wherein the planetary gear system transfers torque from the turbine output shaft to the drive shaft and where the ring gear comprises a flexible ring gear configured to distribute loading among interfaces between the ring gear and the set of planetary gears.2. The air turbine starter of wherein the flexible ring gear comprises a radially inner portion defining a gear face configured to mesh with the set of planetary gears and a radially outer portion mounted to the housing.3. The air turbine starter of wherein the flexible ring gear further ...

AIR TURBINE STARTER WITH DECOUPLER

A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a an output shaft, drive shaft, and a retention mechanism selectively coupling the output shaft to the drive shaft. In a backdrive event, the decoupler decouples the output shaft from the drive shaft. 1. A decoupler assembly for decoupling an output shaft of a starter motor during backdrive , comprising:a tensile fuse having a first end operably coupled to a drive shaft of the starter motor, a threaded portion receivable within an internal threaded portion of the output shaft of the starter motor, and a neck portion located between the first end and the threaded portion; andwherein when a driving torque is transmitted from the drive shaft to the output shaft the tensile fuse is not loaded, when overrunning torque is transmitted below a certain level the tensile fuse is partially loaded and when the overrunning torque reaches a certain level the tensile fuse shears at the neck portion and the threaded portion is threaded in a direction away from the drive shaft.2. The decoupler of claim 1 , further comprising a thread insert operably coupled to the drive shaft and having a threaded portion that receives a threaded portion of the output shaft of the starter motor.3. The decoupler of wherein the tensile fuse is threaded into the output shaft with an opposite hand turn to the threads between the output shaft and the thread insert.4. The decoupler of wherein when the overrunning torque reaches the certain level the output shaft is unthreaded from the thread insert such that it is uncoupled from the drive shaft and the tensile fuse is unthreaded from the output shaft.5. The decoupler of wherein the tensile fuse translates two times the translation of the output shaft.6. The decoupler of claim 4 , further comprising a blocking mechanism configured to bar the output shaft from rethreading with the thread insert.7. An air ...

AIR TURBINE STARTER WITH DECOUPLER

A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a threaded shaft and a retention mechanism selectively coupling the output shaft to the threaded shaft. In a backdrive event, the decoupler decouples the output shaft from a drive shaft. 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 therethrough;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 clutch having a drive shaft that is operably coupled with the gear train;an output shaft with a threaded portion configured to be operably coupled to and rotate with the engine; and a threaded shaft having a first end and a second end operably coupled to the output shaft and where the threaded shaft is selectively receivable and axially moveable with respect to the threaded portion of the drive shaft; and', 'a retention mechanism selectively operably coupling the output member to the first end of the threaded shaft; and, 'a backdrive decoupler, comprisingwherein when driving torque is transmitted from the drive shaft of the clutch to the output shaft the retention mechanism is not loaded, when overrunning torque is transmitted below a certain level the output member, retention mechanism, and threaded shaft are loaded and when the overrunning torque reaches a certain level the retention mechanism uncouples the drive shaft and the first end of the threaded shaft to define a decoupled and separated position where the output member is disengaged from the engine.2. The air turbine starter of wherein the retention mechanism is a shear pin extending axially through a portion of the output member and a portion of the threaded shaft and ...

OPERATING AUXILIARY POWER UNIT DURING OFF-NOMINAL PROPULSION SYSTEM OPERATION

An aircraft system includes a component configured to operate with a minimum power demand. The aircraft system also includes an auxiliary power unit including an engine. The auxiliary power unit is configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode. The auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode. The auxiliary power unit generates a second power output less than the minimum power demand during the standby mode. 1. An aircraft system , comprising:a component configured to operate with a minimum power demand; andan auxiliary power unit comprising an engine;the auxiliary power unit configured to power the component and to operate the engine in a plurality of operating modes including a power mode and a standby mode;wherein the auxiliary power unit generates a first power output at least equal to the minimum power demand during the power mode, and generates a second power output less than the minimum power demand during the standby mode.2. The aircraft system of claim 1 , whereinthe engine includes a rotating assembly;the auxiliary power unit is configured to rotate the rotating assembly at about a first rotational speed during the power mode; andthe auxiliary power unit is configured to rotate the rotating assembly at about a second rotational speed during the standby mode that is less than about eighty-five percent of the first rotational speed.3. The aircraft system of claim 2 , wherein the second rotational speed is between about fifty percent and about eighty percent of the first rotational speed.4. The aircraft system of claim 1 , further comprising a flight control system including the component.5. The aircraft system of claim 1 , wherein the component comprises an actuator.6. The aircraft system of claim 1 , wherein the component comprises a piece of avionics.7. The aircraft system of claim 1 , further ...

DEFORMABLE TURBINE BEARING MOUNT FOR AIR TURBINE STARTER

An air turbine starter includes a support structure and a turbine having a shaft and a rotor that extends away from the shaft in a radial direction. The air turbine starter also includes a mount structure that supports the turbine for rotation relative to the support structure. The mount structure is configured to transfer a force from the turbine to the support structure. The mount structure includes a deformable member that is configured to deform when the force exceeds a predetermined threshold. 1. An air turbine starter comprising:a support structure;a turbine that includes a shaft and a rotor that extends away from the shaft in a radial direction;a mount structure that supports the turbine for rotation relative to the support structure, the mount structure configured to transfer a force from the turbine to the support structure, the mount structure including a deformable member that is configured to deform when the force exceeds a predetermined threshold.2. The air turbine starter of claim 1 , wherein the deformable member is a frangible member that is configured to fracture when the force exceeds the predetermined threshold.3. The air turbine starter of claim 2 , further comprising a cutter member that is fixed to the support structure; andwherein the deformable member is configured to fracture and allow the turbine to move toward and impact the cutter member.4. The air turbine starter of claim 3 , wherein the shaft of the turbine extends along a longitudinal axis;wherein the cutter member includes a plurality of cutters that are arranged about the longitudinal axis, and wherein the plurality of cutters are spaced apart from the rotor with respect to the longitudinal axis; andwherein the deformable member is configured to fracture and allow the turbine to move substantially along the longitudinal axis toward the cutter member so that at least one of the plurality of cutters impacts the rotor.5. The air turbine starter of claim 4 , further comprising a ...

BLEED EXPANDER COOLING WITH TURBINE

An example thermal management system may include a first heat exchanger including a bleed air inlet configured to receive input bleed air from a gas turbine engine and a bleed air outlet configured to output cooled bleed air. A turbine including a turbine inlet may be fluidically coupled to the bleed air outlet. The turbine may be configured to drive a shaft mechanically coupled to the turbine in response to expansion of the cooled bleed air through the turbine. A second heat exchanger may include an expanded bleed air inlet fluidically coupled to a turbine outlet of the turbine. The second heat exchanger may be configured to extract heat from at least one heat source using the expanded bleed air. 1. A thermal management system , comprising:a first heat exchanger comprising a bleed air inlet configured to receive input bleed air from a gas turbine engine and a bleed air outlet configured to output cooled bleed air from the first heat exchanger;an air starter turbine comprising a turbine inlet fluidically coupled to the bleed air outlet of the first heat exchanger and a turbine outlet, wherein the air starter turbine is configured to drive a shaft mechanically coupled to the air starter turbine in response to expansion of the cooled bleed air through the air turbine starter; anda second heat exchanger comprising an expanded bleed air inlet fluidically coupled to the turbine outlet, wherein the second heat exchanger is configured to extract heat from at least one heat source using the expanded bleed air.2. The thermal management system of claim 1 , wherein the at least one heat source comprises at least one of an electric machine claim 1 , an electrical power distribution system claim 1 , a power conversion system claim 1 , power electronics claim 1 , digital electronics claim 1 , or an environmental control system.3. The thermal management system of claim 1 , further comprising a cooling fluid circuit claim 1 , wherein the second heat exchanger is configured to ...

ELECTRICAL SYSTEM FOR AIRCRAFT

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus. 1. An electrical system for a specialized aircraft , the system comprising:an electric generator operatively coupled to an engine of the aircraft;a baseline power bus configured to distribute electricity to one or more baseline electric loads, the electric generator supplying electricity to the baseline power bus when the electric generator is driven by the engine;an electric starter generator operatively coupled to the engine, the electric starter generator being configured to operate as a motor to start the engine and to operate as a generator when driven by the engine; anda supplemental power bus configured to distribute electricity to one or more supplemental electric loads different from the one or more baseline electric loads, the supplemental power bus being independent from the baseline power bus, the electric starter generator supplying electricity to the supplemental power bus when the electric starter generator is driven by the engine.2. The electrical system as defined in claim 1 , wherein the electric generator and the electric starter generator are operatively coupled to the engine via separate mounting pads on a same accessory gearbox.3. The electrical system as defined in claim 1 , wherein the electric starter generator is operatively coupled to the engine via an adaptor gearbox.4. The electrical system as defined in claim 1 , wherein the electric generator and the electric starter generator are housed in a ...

PRESSURIZED AIR SYSTEMS FOR AIRCRAFT AND RELATED METHODS

Pressurized air systems for aircraft and related methods are described herein. An example pressurized air system includes a compressor having a compressor inlet and a compressor outlet. The compressor inlet receives air from a first air source and the compressor outlet supplies pressurized air to an environmental control system (ECS). The pressurized air system includes a turbine having a turbine inlet to receive air from a second air source, a first overrunning clutch operatively coupled between an output shaft of an accessory gearbox and the compressor, the accessory gearbox operatively coupled to a drive shaft extending from an engine of the aircraft, and a second overrunning clutch operatively coupled between the compressor and the turbine. The first and second overrunning clutches enable the accessory gearbox to drive the compressor during a first mode of operation and enable the turbine to drive the compressor during a second mode of operation. 1. A pressurized air system for an aircraft , the pressurized air system comprising:a compressor having a compressor inlet and a compressor outlet, the compressor inlet to receive air from a first air source and the compressor outlet to supply pressurized air to an environmental control system (ECS) of the aircraft;a turbine having a turbine inlet to receive air from a second air source;a first overrunning clutch operatively coupled between an output shaft of an accessory gearbox and the compressor, the accessory gearbox operatively coupled to a drive shaft extending from an engine of the aircraft; anda second overrunning clutch operatively coupled between the compressor and the turbine, the first and second overrunning clutches to enable the accessory gearbox to drive the compressor during a first mode of operation and to enable the turbine to drive the compressor during a second mode of operation.2. The pressurized air system of claim 1 , further including a third overrunning clutch operatively coupled between a ...

SYSTEM AND METHOD FOR CONTROLLING DUAL STARTER AIR VALVE

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor. 1. A method of controlling a rotational speed of a gas turbine engine during start-up , comprising:receiving, by a valve assembly, an input airflow having an input pressure, the valve assembly including a first valve and a second valve;measuring the rotational speed of the gas turbine engine;controlling, by a full authority digital engine control (FADEC), an output pressure of an output airflow by controlling a position at least one of the first valve and the second valve based on the rotational speed of the gas turbine engine; anddelivering the output airflow to an air turbine starter coupled to the gas turbine engine.2. The method of claim 1 , wherein the first valve comprises a torque motor servovalve and wherein the positioning the at least one of the first valve and the second valve further comprises delivering a current to the torque motor servovalve to adjust the position of the first valve.3. The method of claim 2 , wherein the positioning the at least one of the first valve and the second valve further comprises locking the second valve in an open position while adjusting the position of the first valve.4. The method of claim 1 , wherein the second valve comprises a solenoid and wherein the positioning the at least one of the first valve and the second valve further comprises pulse width modulating the solenoid between an on state and an off state.5. The method of claim 4 , wherein ...

Air starter for turbine engine

FIELD: engines and pumps. SUBSTANCE: air starter comprises front case (12), rear case (14), exhaust gas flow circular channel (32) and cylindrical grate (44) of said channel (32). The latter is open between front case rear end and rear case front end. Discharge grate front and rear ends comprises means (48, 52) of retention of front case (12) and rear case (14) in axial direction towards grate (44). Said retention means (52) allows relative rotation of grate (44) and said case (14). Rotation forces can be dissipated to allow rotation of front case relative to rear case. EFFECT: decreased weight, higher reliability, integrity of starter at turbine blast. 13 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 518 719 C2 (51) МПК F02C 7/277 (2006.01) F01D 21/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2010103837/06, 04.02.2010 (24) Дата начала отсчета срока действия патента: 04.02.2010 (72) Автор(ы): ЛЕ СЭН Рашель (FR) (73) Патентообладатель(и): МИКРОТЮРБО (FR) Приоритет(ы): (30) Конвенционный приоритет: (43) Дата публикации заявки: 10.08.2011 Бюл. № 22 R U 05.02.2009 FR 0950709 (45) Опубликовано: 10.06.2014 Бюл. № 16 2 5 1 8 7 1 9 R U Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54) ВОЗДУШЫЙ СТАРТЕР ДЛЯ ТУРБОДВИГАТЕЛЯ (57) Реферат: Воздушный стартер для турбодвигателя относительное вращение решетки (44) и этого содержит передний корпус (12), задний корпус корпуса (14). Стартер по изобретению может в (14), кольцевой тракт (32) потока выходящих большей степени удовлетворять газов и цилиндрическую выпускную решетку (44) сертификационным требованиям и быть легче и тракта (32) потока выходящих газов. Кольцевой надежнее. В результате взрыва турбины стартера тракт (32) открыт между задним концом средство удерживания в осевом направлении переднего корпуса и передним концом заднего корпусов к решетке сохраняет целостность корпуса. ...

用于发动机起动器中的部件的润滑系统

一种空气涡轮起动器，包括具有分隔器结构的壳体，分隔器结构将壳体分隔为湿室和空气室。空气涡轮起动器还包括轴承组件，涡轮构件，第一驱动轴和第二驱动轴，第二驱动轴将涡轮构件与旋转组件连接。润滑剂供应部分具有流体地联接至湿室的至少一个供应入口和流体地联接至轴承组件的至少一个供应出口，从而可以将来自湿室的润滑剂供应到轴承组件。

Gas turbine engine with a starter mounted on the gear unit

The engine has an auxiliary gearbox (12) connected mechanically to a shaft (30) of the engine for driving auxiliary machines. An air starter (10) having an oil enclosure is mounted on the gearbox, where the oil enclosure and the gearbox are communicated with each other such that lubricating oil in the starter is distributed from the gearbox. The oil enclosure is pressurized by an air source e.g. bearing's pressurization enclosure, that is independent from the gearbox. An air return conduit (43) is connected on a wall (124) of the gearbox.