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公开(公告)号：US20180328287A1
公开(公告)日：2018-11-15
申请号：US15593748
申请日：2017-05-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , James William Simunek , Jeffrey Donald Clements , Brandon Wayne Miller , Sridhar Adibhatla
CPC classification number: F02C7/36 , F02C3/067 , F02C7/22 , F02C9/20 , F04D29/563 , F05D2220/32 , F05D2270/304 , F05D2270/31
Abstract: The present disclosure is directed to a method of control of a gas turbine engine comprising a fan section coupled to a low turbine together defining a low spool, an intermediate compressor coupled to an intermediate turbine together defining an intermediate spool, and a high compressor coupled to a high turbine together defining a high spool. The method includes providing an intermediate spool speed to low spool speed characteristic curve to a controller; providing a commanded power output to the controller; providing one or more of an environmental condition to the controller; determining, via the controller, a commanded fuel flow rate; determining, via the controller, a commanded intermediate compressor loading; and generating an actual power output of the engine, wherein the actual power output is one or more of an actual low spool speed, an actual intermediate spool speed, an actual high spool speed, and an actual engine pressure ratio.
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12.发明申请公开(公告)号：US20180283278A1
公开(公告)日：2018-10-04
申请号：US15478949
申请日：2017-04-04
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
CPC classification number: F01D21/003 , F01D21/14 , F01D25/12 , F02C9/00 , F05D2220/323 , F05D2260/80 , F05D2270/11 , F05D2270/112 , F05D2270/3032
Abstract: Systems and methods for adjusting an operating parameter of a machine based on an operating state of a component of the machine are provided. A method may be implemented by an electronic control unit (ECU) of the machine and includes determining that a performance of the machine has degraded. The method further includes selecting a predetermined adjustment to the operating parameter, wherein the selected predetermined adjustment reduces an effect of the operating state of the component on the performance of the machine, and operating the machine using the selected predetermined adjustment to the operating parameter.
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公开(公告)号：US09758252B2
公开(公告)日：2017-09-12
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
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公开(公告)号：US20170254216A1
公开(公告)日：2017-09-07
申请号：US15059116
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Jeffrey Wayne Litzler
CPC classification number: F01D21/003 , F01D21/14 , F02C6/08 , F02C9/18 , F05D2260/80 , F05D2270/09
Abstract: A pipe fault detection system is provided for a gas turbine engine having a compressor and a turbine. The pipe fault detection system includes a cooling manifold configured to direct cooling air from the compressor to the turbine. The cooling manifold includes at least two cooling pipes, a sensor configured to detect an operating condition indicative of a pipe break, and a controller configured to control the amount of cooling air through the cooling manifold in response to the operating condition detected by the sensor.
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公开(公告)号：US20170234224A1
公开(公告)日：2017-08-17
申请号：US15044475
申请日：2016-02-16
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
Abstract: A method of modulating cooling flow to an engine component based on a health of the component is provided. The method includes determining a cooling flow requirement of the engine component for each of a plurality of operating conditions and channeling the determined required flow to the engine component during each respective operating condition of the plurality of operating conditions. The method also includes assessing a health of the engine component. The method further includes modifying the determined cooling flow requirement based on the assessed health of the engine component, and supplying the modified cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.
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Patent Agency Ranking
公开(公告)号：US20170138781A1
公开(公告)日：2017-05-18
申请号：US14943429
申请日：2015-11-17
Applicant: General Electric Company
Inventor： Sridhar Adibhatla
Abstract: Parameter measurement systems including improved sensor calibration are provided herein. The measurement system includes a first sensor with a first output signal including a plurality of output characteristics, at least one output characteristic being deficient for measuring a desired parameter and at least one output characteristic being suitable for measuring the desired parameter. The measurement system also includes a second sensor with a second output signal comprising at least some of the plurality of output characteristics, the at least one deficient characteristic of the first output signal being suitable in the second output signal for measuring the desired parameter. The measurement system further includes a processor programmed to calibrate the first output signal using the second output signal to generate a third output signal including the at least one suitable characteristic of the first output signal and the at least one suitable characteristic of the second output signal.
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公开(公告)号：US20160311546A1
公开(公告)日：2016-10-27
申请号：US15077731
申请日：2016-03-22
Applicant: General Electric Company
Inventor： Sridhar Adibhatla , Steven Edward Nolte , Gerhard Walter Moeller , Christopher Timothy Gallagher , John William Hanify , Grant Alan Ingram
Abstract: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.
Abstract translation: 提供了一种用于减小涡轮发动机的多个转子叶片和涡轮发动机的护罩之间的涡轮机间隙的方法。 该方法包括确定飞机处于第一飞行状态，并且将涡轮机间隙间隙调整到与第一飞行状态相关联的第一间隙间隙距离。 该方法还包括确定对第二飞行状态的需求，以及调整发动机对功率参数的第一预定变化的第一发动机响应性的发动机响应性。 该方法还包括将引擎响应性从第一发动机响应级别降低到用于发动机的功率参数的第二预定变化的第二发动机响应性水平，并且在第二预定变化期间关闭与护罩相关联的间隙控制阀 发动机的功率参数。
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公开(公告)号：US20140136030A1
公开(公告)日：2014-05-15
申请号：US14159490
申请日：2014-01-21
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Harry Kirk Mathews, JR. , Sridhar Adibhatla , Jeffrey Russell Bult
CPC classification number: B64C19/00 , B64D31/06 , F05D2260/80 , H04B7/18506
Abstract: A method of operating an aircraft system includes receiving flight information and trajectory intent information other than current values by an engine control system associated with an engine of the aircraft system from a flight control system associated with the aircraft system; and operating an engine associated with the engine control system using the received non-current information. An aircraft includes an engine positioned on the aircraft; a full authority digital engine controller (FADEC) communicatively coupled to the engine; and a flight control system positioned on the aircraft and communicatively coupled to the FADEC, the flight control system configured to transmit other than current values of flight information and trajectory intent information to the FADEC and to receive other than current values of at least one of engine health and parameters used to estimate engine health from at least one of the FADEC and a separate flight control center positioned offboard the aircraft.
Abstract translation: 一种操作飞行器系统的方法包括从与飞行器系统相关联的飞行控制系统的飞行器系统的发动机相关联的发动机控制系统接收除当前值以外的飞行信息和轨迹意图信息; 以及使用所接收的非当前信息来操作与所述发动机控制系统相关联的发动机。 飞机包括位于飞机上的发动机; 通信地耦合到发动机的全权限数字引擎控制器（FADEC）; 以及飞行控制系统，其定位在所述飞行器上并且通信地耦合到所述FADEC，所述飞行控制系统被配置为向所述FADEC发送除飞行信息和轨迹意图信息的当前值之外的其它值，并且接收不同于发动机中的至少一个的当前值 卫生和参数用于从至少一个FADEC和位于飞机外侧的单独的飞行控制中心估计发动机健康。
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公开(公告)号：US11447263B2
公开(公告)日：2022-09-20
申请号：US16179000
申请日：2018-11-02
Applicant: General Electric Company
Abstract: A method of operating a fuel oxygen reduction unit for a vehicle or a gas turbine engine of the vehicle is provided. The fuel oxygen reduction unit including a contactor and a fuel gas separator, and further defining a stripping gas flowpath in flow communication with a stripping gas inlet of the contactor and a stripping gas outlet of the fuel gas separator. The method includes receiving data indicative of a parameter of a stripping gas flow through the stripping gas flowpath or of a component in flow communication with the stripping gas flow through the stripping gas flowpath; and determining an operability condition of the fuel oxygen reduction unit, or a component operable with the fuel oxygen reduction unit, based on the data received indicative of the parameter of the stripping gas flow or of the component in flow communication with the stripping gas flow.
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公开(公告)号：US20210341145A1
公开(公告)日：2021-11-04
申请号：US16864357
申请日：2020-05-01
Applicant: General Electric Company
Inventor： Daniel Alan Niergarth , Sridhar Adibhatla , Ethan Patrick O'Connor
Abstract: A fuel delivery system for a gas turbine engine includes a fuel source; a draw pump downstream of the fuel source for generating a liquid fuel flow from the fuel source; a main fuel pump downstream of the draw pump; and a fuel oxygen reduction unit downstream of the draw pump and upstream of the main fuel pump. The fuel oxygen reduction unit includes a stripping gas line; a contactor in fluid communication with the stripping gas line and the draw pump for forming a fuel/gas mixture, wherein the contactor receives an inlet fuel flow from the draw pump; a separator in fluid communication with the contactor, the separator receives the fuel/gas mixture and separates the fuel/gas mixture into an outlet stripping gas flow and an outlet fuel flow at a location upstream of the main fuel pump; a catalyst disposed downstream of the separator, the catalyst receives and treats the outlet stripping gas flow, wherein a stripping gas stream flows out the catalyst; and a water removal component disposed between the catalyst and the contactor, wherein the water removal component removes water from the stripping gas stream.
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