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公开(公告)号：US11795882B2
公开(公告)日：2023-10-24
申请号：US18152991
申请日：2023-01-11
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
CPC classification number: F02C7/36 , F02C7/06 , F05D2240/54 , F05D2240/61 , F05D2250/711 , F05D2300/603
Abstract: A turbomachine engine includes a core engine having one or more compressor sections, one or more turbine sections that includes a power turbine, and a combustion chamber in flow communication with the compressor sections and turbine sections. The turbomachine engine also includes a shaft coupled to the power turbine and characterized by a midshaft rating (MSR) between two hundred (ft/sec)1/2 and three hundred (ft/sec)1/2. In one aspect, the shaft has a redline speed between fifty and two hundred fifty feet per second (ft/sec). In another aspect, the shaft has a length L, an outer diameter D, and a ratio of L/D between twelve and thirty-seven.
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公开(公告)号：US11346243B2
公开(公告)日：2022-05-31
申请号：US15491638
申请日：2017-04-19
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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公开(公告)号：US10017270B2
公开(公告)日：2018-07-10
申请号：US14879217
申请日：2015-10-09
Applicant: General Electric Company
IPC: B64D33/02 , B64D27/18 , B64D27/24 , B64D27/26 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/32 , F04D29/36 , F04D29/52 , F04D29/54 , B64C1/16 , B64C21/06 , B64D27/20 , B64D29/04 , B64D27/02
CPC classification number: B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
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公开(公告)号：US20170114664A1
公开(公告)日：2017-04-27
申请号：US14920993
申请日：2015-10-23
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
CPC classification number: H02K7/1823 , F01D5/026 , F01D15/10 , F01D25/04 , F02C3/04 , F02C6/14 , F02C7/22 , F03D7/0296 , F05D2220/32 , F05D2240/35 , F05D2260/96 , H02K7/003
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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公开(公告)号：US20170081035A1
公开(公告)日：2017-03-23
申请号：US14859514
申请日：2015-09-21
Applicant: General Electric Company
CPC classification number: B64D27/14 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/00 , B64D29/04 , B64D2027/264 , B64D2033/0226
Abstract: A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft.
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Patent Agency Ranking
公开(公告)号：US20240044261A1
公开(公告)日：2024-02-08
申请号：US18483696
申请日：2023-10-10
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
CPC classification number: F01D25/04 , F01D15/10 , F05D2260/96 , F02C3/04
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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公开(公告)号：US10358228B2
公开(公告)日：2019-07-23
申请号：US15794648
申请日：2017-10-26
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
Abstract: An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft.
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公开(公告)号：US09884687B2
公开(公告)日：2018-02-06
申请号：US14859556
申请日：2015-09-21
Applicant: General Electric Company
Inventor： Patrick Michael Marrinan , Thomas Lee Becker , Kurt David Murrow , Jixian Yao
CPC classification number: B64D27/14 , B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/20 , B64D29/04 , B64D33/02 , Y02T50/166
Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine.
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公开(公告)号：US20170222518A1
公开(公告)日：2017-08-03
申请号：US15491638
申请日：2017-04-19
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
CPC classification number: H02K7/1823 , F01D5/026 , F01D15/10 , F01D25/04 , F02C3/04 , F02C6/14 , F02C7/22 , F03D7/0296 , F05D2220/32 , F05D2240/35 , F05D2260/96 , H02K7/003
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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公开(公告)号：US20170114665A1
公开(公告)日：2017-04-27
申请号：US15018966
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
IPC: F01D25/04 , F02C7/22 , F02C7/04 , H02P9/00 , F16F15/14 , F16F15/16 , H02K5/24 , H02P23/04 , F02C3/04 , F01D15/10
CPC classification number: F01D25/04 , F01D15/10 , F02C3/04 , F02C7/04 , F02C7/22 , F02C7/36 , F05D2220/32 , F05D2240/35 , F05D2260/96 , F16F15/00 , F16F15/12 , F16F15/14 , F16F15/16 , F16F15/18 , H02K5/24 , H02P9/007 , H02P21/05 , H02P23/04 , H02P23/26 , Y02T50/671
Abstract: The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air in the combustion chamber and ignited so as to raise a temperature and energy level of the pressurized air. The turbine is operatively coupled to the combustion chamber so as to receive combustion products that flow from the combustion chamber. The generator is coupled to the turbine via a shaft. Thus, the torsional damper is configured to dampen torsional oscillations of the generator. Moreover, the controller is configured to provide additional damping control to the generator.
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