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公开(公告)号：US11306654B2
公开(公告)日：2022-04-19
申请号：US16695290
申请日：2019-11-26
Applicant: United Technologies Corporation
Inventor： Stephen A. Witalis , Ramesh Rajagopalan , Subhradeep Chowdhury
Abstract: An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with an idle fuel burn schedule in a taxi mode of the aircraft and operate the second gas turbine engine with a sub-idle fuel burn schedule in the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.
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公开(公告)号：US11203950B2
公开(公告)日：2021-12-21
申请号：US15879804
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
Abstract: An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.
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公开(公告)号：US10557418B2
公开(公告)日：2020-02-11
申请号：US15879718
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
Abstract: An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.
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公开(公告)号：US11199139B2
公开(公告)日：2021-12-14
申请号：US16359249
申请日：2019-03-20
Applicant: United Technologies Corporation
Inventor： Ramesh Rajagopalan , Subhradeep Chowdhury , Stephen A Witalis , William C. Lamberti
Abstract: An engine system for an aircraft includes a first gas turbine engine, a second gas turbine engine, and a control system. The control system is configured to operate the first gas turbine engine with an idle fuel burn schedule in a taxi mode of the aircraft and dry crank the second gas turbine engine in a first pre-takeoff portion of the taxi mode to cool the second gas turbine engine absent fuel burn by the second gas turbine engine. The control system operates the second gas turbine engine with a sub-idle fuel burn schedule in a second pre-takeoff portion of the taxi mode of the aircraft. The sub-idle fuel burn schedule includes a reduction of the idle fuel burn schedule. A fuel flow of the first gas turbine engine and the second gas turbine engine is increased above the idle fuel burn schedule prior to takeoff of the aircraft.
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公开(公告)号：US20190226407A1
公开(公告)日：2019-07-25
申请号：US15879718
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
CPC classification number: F02C9/00 , F05D2220/323 , F05D2260/80 , F05D2270/09 , F05D2270/094 , F05D2270/46 , F05D2270/60 , F05D2270/71 , F05D2270/821 , G05B13/024 , G05B13/041 , G05B23/0291
Abstract: An engine control system includes an electronic hardware engine controller and an actuator that operates at different positions to control operation of an engine. An actuator sensor measures an actuator position, and the engine controller generates a synthesized actuator position. In response to detecting a faulty actuator, a faulty actuator sensor, or both, the engine controller adjusts the position of the actuator based on the synthesized actuator position.
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Patent Agency Ranking
公开(公告)号：US20190226354A1
公开(公告)日：2019-07-25
申请号：US15879849
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
Abstract: An engine control system includes an electronic hardware engine controller in signal communication with at least one engine sensor, which measures an engine operating parameter (Ycrtr_t). The engine controller generates a synthesized engine operating parameter (Ycrtr) calculates an error (ERRcrtr) between the engine operating parameter (Ycrtr_t) and the synthesized engine operating parameter (Ycrtr). The engine controller further determines a corrector error parameter (Xcrtr) and determines a faulty sensor among the at least one engine sensor based on a comparison between the error value (ERRcrtr) and the corrector error parameter (Xcrtr).
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公开(公告)号：US11319834B2
公开(公告)日：2022-05-03
申请号：US15879849
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
Abstract: An engine control system includes an electronic hardware engine controller in signal communication with at least one engine sensor, which measures an engine operating parameter (Ycrtr_t). The engine controller generates a synthesized engine operating parameter (Ycrtr) calculates an error (ERRcrtr) between the engine operating parameter (Ycrtr_t) and the synthesized engine operating parameter (Ycrtr). The engine controller further determines a corrector error parameter (Xcrtr) and determines a faulty sensor among the at least one engine sensor based on a comparison between the error value (ERRcrtr) and the corrector error parameter (Xcrtr).
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公开(公告)号：US11047257B2
公开(公告)日：2021-06-29
申请号：US15656444
申请日：2017-07-21
Applicant: United Technologies Corporation
Inventor： Subhradeep Chowdhury , David M. Bostwick , David Gelwan , Frederick M. Schwarz
IPC: F01D19/02 , B64D27/12 , F01D25/34 , F02C6/20 , F02C7/277 , F02C9/00 , B64D41/00 , B64F1/36 , F02C3/04
Abstract: 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.
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公开(公告)号：US20190226353A1
公开(公告)日：2019-07-25
申请号：US15879804
申请日：2018-01-25
Applicant: United Technologies Corporation
Inventor： Boris Karpman , Richard P. Meisner , Subhradeep Chowdhury
Abstract: An engine control system includes an electronic hardware engine controller in signal communication with an actuator and an engine sensor. The actuator operates at a plurality of different positions to control operation of an engine. The engine sensor measures an engine operating parameter. The engine controller generates a synthesized engine operating parameter, and adjusts the position of the actuator based on the synthesized engine operating parameter in response to detecting a faulty engine sensor.
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公开(公告)号：US20180023413A1
公开(公告)日：2018-01-25
申请号：US15656444
申请日：2017-07-21
Applicant: United Technologies Corporation
Inventor： Subhradeep Chowdhury , David M. Bostwick , David Gelwan , Frederick M. Schwarz
CPC classification number: F01D19/02 , B64D27/12 , B64D41/00 , B64D2041/002 , B64F1/364 , F01D25/34 , F02C3/04 , F02C6/20 , F02C7/277 , F02C9/00 , F05D2220/323 , F05D2220/50 , F05D2260/85 , F05D2270/303
Abstract: 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.
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