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公开(公告)号：US20190264618A1
公开(公告)日：2019-08-29
申请号：US15905912
申请日：2018-02-27
发明人： Andre M. Ajami , Sami Chukrallah , James D. Hunter
摘要： A fuel assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fuel valve that meters flow of fluid between a combustor and a fuel supply, and a controller in communication with the fuel assembly. The controller is programmed to receive data corresponding to a present rotational speed of a gas turbine engine component and data corresponding to at least one present flight condition, and is programmed to cause a flow rate from the fuel valve to change in response to determining that a rate of change in an acceleration rate relating to the present rotational speed meets at least one predetermined threshold. At least one predetermined threshold relates to an engine light-off event of the combustor and is based upon the at least one present flight condition.
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公开(公告)号：US20160195025A1
公开(公告)日：2016-07-07
申请号：US14911318
申请日：2014-08-26
CPC分类号： F02C9/263 , F02C9/28 , F05D2260/80 , F05D2270/0831 , F05D2270/09 , F05D2270/092 , F05D2270/303 , F05D2270/309 , G01K3/10 , G01K13/02 , G01K2013/024
摘要： A method includes receiving an indication of exhaust gas temperature (EGT) for a gas turbine engine, and determining, by at least one processor, based on the received indication of the EGT, a representation of a second derivative with respect to time of the EGT. The method further includes comparing the representation of the second derivative of the EGT to a threshold value, and determining, based on the comparing, an engine flameout condition of the gas turbine engine. In some embodiments, the at least one processor can determine a representation of a first derivative with respect to time of the EGT. The representation of the first derivative of the EGT can be compared to a threshold value, determined based on the received indication of the EGT, to determine the engine flameout condition.
摘要翻译： 一种方法包括接收燃气涡轮发动机的排气温度（EGT）的指示，以及由至少一个处理器基于接收到的EGT指示确定相对于EGT的时间的二阶导数的表示 。 该方法还包括将EGT的二阶导数的表示与阈值进行比较，并且基于比较来确定燃气涡轮发动机的发动机熄火状态。 在一些实施例中，至少一个处理器可以确定关于EGT的时间的一阶导数的表示。 可以将EGT的一阶导数的表示与基于EGT的接收指示确定的阈值进行比较，以确定发动机熄火状况。
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公开(公告)号：US11174793B2
公开(公告)日：2021-11-16
申请号：US16135455
申请日：2018-09-19
摘要： A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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公开(公告)号：US11015535B2
公开(公告)日：2021-05-25
申请号：US15905912
申请日：2018-02-27
发明人： Andre M. Ajami , Sami Chukrallah , James D. Hunter
摘要： A fuel assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fuel valve that meters flow of fluid between a combustor and a fuel supply, and a controller in communication with the fuel assembly. The controller is programmed to receive data corresponding to a present rotational speed of a gas turbine engine component and data corresponding to at least one present flight condition, and is programmed to cause a flow rate from the fuel valve to change in response to determining that a rate of change in an acceleration rate relating to the present rotational speed meets at least one predetermined threshold. At least one predetermined threshold relates to an engine light-off event of the combustor and is based upon the at least one present flight condition.
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公开(公告)号：US20200333002A1
公开(公告)日：2020-10-22
申请号：US16390315
申请日：2019-04-22
发明人： Sami Chukrallah , Andre M. Ajami , Robert B. Davis
摘要： A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combusto. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.
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公开(公告)号：US11199325B2
公开(公告)日：2021-12-14
申请号：US16390315
申请日：2019-04-22
发明人： Sami Chukrallah , Andre M. Ajami , Robert B. Davis
摘要： A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath, a turbine section fluidly connected to the combustor via the primary flowpath, and a plurality of fuel injectors disposed within the combustor. The plurality of fuel injectors including at least one start fuel injector. Also included is a controller having a memory and processor. The memory stores instructions configured to cause the at least one start fuel injector to pulse fuel through the start injector nozzle, thereby preventing stagnant fuel in the start injector nozzle from exceed a coking temperature threshold.
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公开(公告)号：US20210254545A1
公开(公告)日：2021-08-19
申请号：US16791106
申请日：2020-02-14
发明人： Andre M. Ajami , Ryan W. Hunter , Javier A. Cue
摘要： An engine system includes a gas turbine engine with a first compressor, a first combustor, and a first turbine. The engine system also includes a secondary power unit with a second compressor, a second combustor, a second turbine, a third compressor coupled to the second compressor, and an electric motor-generator, where the secondary power unit is coupled to the gas turbine engine. A controller is operable to determine an operating mode of the engine system, select an input energy source and an output type of the secondary power unit based on the operating mode, control the secondary power unit based on the input energy source and the output type as selected, detect a change in the operating mode of the engine system, and modify the input energy source and/or the output type of the secondary power unit based on the change in the operating mode.
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公开(公告)号：US20160090915A1
公开(公告)日：2016-03-31
申请号：US14787068
申请日：2014-04-30
发明人： Eric L. Wolff , Brent L. Sherill , Andre M. Ajami , Kenneth W. Winston , Victor Pascu , Phillip Vessa , Nelson DaCunha
CPC分类号： F02C7/268 , B64D41/00 , B64D2033/0213 , F01D19/00 , F02C7/04 , F05D2220/50 , F05D2260/85
摘要： A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine. The engine controller determines an intermediate door position based upon one or more engine start factors. The door controller operates the actuator to open the inlet door to the intermediate door position based on the one or more engine start factors.
摘要翻译： 燃气涡轮发动机进气门控制系统包括致动器，发动机控制器和门控制器。 致动器打开和关闭燃气涡轮发动机的入口门。 发动机控制器基于一个或多个发动机启动因素确定中间门位置。 门控制器操作致动器，以基于一个或多个发动机启动因素将入口门打开到中间门位置。
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公开(公告)号：US20200088103A1
公开(公告)日：2020-03-19
申请号：US16135455
申请日：2018-09-19
摘要： A starter assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a fluid-actuated starter coupled to a spool, and a controller operable to cause a reduction in torque output of the starter in response to determining that a first predefined threshold is met. The first predefined threshold relates to an engine operational condition. A method for starting a gas turbine engine is also disclosed.
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