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公开(公告)号：US20180354635A1
公开(公告)日：2018-12-13
申请号：US15618257
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Nicholas Adam Wagner , Daniel E. Bergsten , David Allen Gutz
Abstract: A hybrid electric propulsion system includes a gas turbine engine and an electric machine coupled to the gas turbine engine. A method for operating the propulsion system includes determining, by one or more computing devices, a baseline power output for the gas turbine engine; operating, by the one or more computing devices, the gas turbine engine to provide the baseline power output; determining, by the one or more computing devices, a desired power output greater than or less than the baseline power output; and providing, by the one or more computing devices, power to, or extracting, by the one or more computing devices, power from, the gas turbine engine using the electric machine such that an effective power output of the gas turbine engine matches the determined desired power output.
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公开(公告)号：US20190002115A1
公开(公告)日：2019-01-03
申请号：US15597597
申请日：2017-05-17
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Michael Thomas Gansler , Sridhar Adibhatla , Daniel E. Bergsten , Nicholas Adam Wagner , David Allen Gutz
Abstract: A method of operating a hybrid-electric propulsion system for an aircraft includes determining a flight phase parameter for the aircraft is equal to a first value, and operating the hybrid-electric propulsion system in an electric charge mode in response to determining the flight phase parameter for the aircraft is equal to the first value. The method also includes determining the flight phase parameter for the aircraft is equal to a second value different from the first value, and operating the hybrid-electric propulsion system in an electric discharge mode in response to determining the flight phase parameter for the aircraft is equal to the second value.
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公开(公告)号：US10006375B1
公开(公告)日：2018-06-26
申请号：US15646592
申请日：2017-07-11
Applicant: General Electric Company
Inventor： Nicholas Adam Wagner , Daniel E. Bergsten , David Allen Gutz
IPC: B64C13/00 , F02C9/46 , B64C27/14 , B64D27/24 , B64D27/10 , F02C9/28 , F02C6/20 , H02P3/14 , H02P3/12 , B64D27/02
CPC classification number: F02C9/46 , B64C27/14 , B64D27/10 , B64D27/24 , B64D31/06 , B64D45/00 , B64D2027/026 , F02C6/00 , F02C6/206 , F02C9/28 , F02K5/00 , F05D2220/329 , F05D2220/76 , H02P3/12 , H02P3/14 , H02P3/18 , H02P9/08
Abstract: A hybrid electric propulsion system includes a turbomachine, an electric machine coupled to the turbomachine, and a propulsor coupled to the turbomachine. A method for operating the hybrid electric propulsion system includes operating the turbomachine to drive the propulsor; receiving data indicative of a failure condition of the hybrid electric propulsion system; reducing a fuel flow to a combustion section of the turbomachine in response to receiving the data indicative of the failure condition; and extracting power from the turbomachine using the electric machine to slow down one or more rotating components of the turbomachine in response to receiving the data indicative of the failure condition.
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4.发明申请公开(公告)号：US20180086474A1
公开(公告)日：2018-03-29
申请号：US15278413
申请日：2016-09-28
Applicant: General Electric Company
Inventor： David Allen Gutz
CPC classification number: B64D37/00 , B64D27/10 , F02C9/00 , F02C9/26 , F02C9/28 , F02C9/42 , F02C9/44 , G06F15/00
Abstract: A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is configured for determining first motion sensor data indicating motion of the aircraft along at least one axis of the first orthogonal coordinate system. The system further includes a second engine controller comprising a second motion sensor spaced apart from the first motion sensor. The second motion sensor defines a second orthogonal coordinate system, and is configured for determining second motion sensor data indicating motion of the aircraft along at least one axis of the second orthogonal coordinate system. In addition, the second engine controller is communicatively coupled to the first engine controller such that the first engine controller receives the second motion sensor data.
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公开(公告)号：US11053861B2
公开(公告)日：2021-07-06
申请号：US15059378
申请日：2016-03-03
Applicant: General Electric Company
Inventor： David Anthony Moster , William James Mailander , David Allen Gutz
Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
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Patent Agency Ranking
公开(公告)号：US10800536B2
公开(公告)日：2020-10-13
申请号：US15618257
申请日：2017-06-09
Applicant: General Electric Company
Inventor： Nicholas Adam Wagner , Daniel E. Bergsten , David Allen Gutz
Abstract: A hybrid electric propulsion system includes a gas turbine engine and an electric machine coupled to the gas turbine engine. A method for operating the propulsion system includes determining, by one or more computing devices, a baseline power output for the gas turbine engine; operating, by the one or more computing devices, the gas turbine engine to provide the baseline power output; determining, by the one or more computing devices, a desired power output greater than or less than the baseline power output; and providing, by the one or more computing devices, power to, or extracting, by the one or more computing devices, power from, the gas turbine engine using the electric machine such that an effective power output of the gas turbine engine matches the determined desired power output.
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7.发明授权公开(公告)号：US10252812B2
公开(公告)日：2019-04-09
申请号：US15278413
申请日：2016-09-28
Applicant: General Electric Company
Inventor： David Allen Gutz
IPC: G05D1/00 , G05D3/00 , G05D13/00 , G05D1/08 , B64D37/00 , B64D27/10 , F02C9/44 , F02C9/00 , F02C9/26 , F02C9/28 , F02C9/42 , G06F15/00
Abstract: A system for an aircraft having a first gas turbine engine and a second gas turbine engine includes a first engine controller comprising a first motion sensor. The first motion sensor defines a first orthogonal coordinate system, and is configured for determining first motion sensor data indicating motion of the aircraft along at least one axis of the first orthogonal coordinate system. The system further includes a second engine controller comprising a second motion sensor spaced apart from the first motion sensor. The second motion sensor defines a second orthogonal coordinate system, and is configured for determining second motion sensor data indicating motion of the aircraft along at least one axis of the second orthogonal coordinate system. In addition, the second engine controller is communicatively coupled to the first engine controller such that the first engine controller receives the second motion sensor data.
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公开(公告)号：US10302020B2
公开(公告)日：2019-05-28
申请号：US15375547
申请日：2016-12-12
Applicant: General Electric Company
Inventor： David Allen Gutz , Robert Edward Goeller
Abstract: A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of the gas turbine engine that indicates a difference between a desired rotational speed and an actual rotational speed. The method also includes integrating the first rate of change of fuel flow demand to determine a tracking error fuel flow demand. In addition, the method includes summing the control initiated fuel flow demand and tracking error fuel flow demand to determine a composite fuel flow demand. The method also includes controlling a fuel flow to the gas turbine engine based, at least in part, on the composite fuel flow demand.
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公开(公告)号：US20180163638A1
公开(公告)日：2018-06-14
申请号：US15375547
申请日：2016-12-12
Applicant: General Electric Company
Inventor： David Allen Gutz , Robert Edward Goeller
CPC classification number: F02C9/28 , B64D37/005 , F05D2270/301 , F05D2270/303 , F05D2270/304 , F05D2270/309 , G05B15/02
Abstract: A computer-implemented method for controlling a fuel flow to a gas turbine engine of an aircraft includes determining a control initiated fuel flow demand that is based, at least in part, on an operator command. In addition, the method includes determining a first rate of change of fuel flow demand based, at least in part, on a tracking error of the gas turbine engine that indicates a difference between a desired rotational speed and an actual rotational speed. The method also includes integrating the first rate of change of fuel flow demand to determine a tracking error fuel flow demand. In addition, the method includes summing the control initiated fuel flow demand and tracking error fuel flow demand to determine a composite fuel flow demand. The method also includes controlling a fuel flow to the gas turbine engine based, at least in part, on the composite fuel flow demand.
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公开(公告)号：US20170254295A1
公开(公告)日：2017-09-07
申请号：US15059378
申请日：2016-03-03
Applicant: General Electric Company
Inventor： David Anthony Moster , William James Mailander , David Allen Gutz
CPC classification number: F02C9/00 , F01D21/02 , F02K3/06 , Y02T50/671
Abstract: In accordance with one exemplary embodiment of the present disclosure, a method for providing overspeed protection for a gas turbine engine is provided. The gas turbine engine may include an engine core and an engine shaft. The method may include determining an overspeed condition of the engine. The overspeed condition may be indicative of an above normal rotational speed of the engine shaft. The method may also include reducing an airflow through the engine core of the gas turbine engine in response to the determined overspeed condition to reduce the rotational speed of the engine shaft.
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