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公开(公告)号：US20220282637A1
公开(公告)日：2022-09-08
申请号：US17749805
申请日：2022-05-20
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：US10247017B2
公开(公告)日：2019-04-02
申请号：US15197254
申请日：2016-06-29
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Thomas Lee Becker , Daniel Alan Niergarth , Bugra Han Ertas
Abstract: A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.
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公开(公告)号：US09995175B2
公开(公告)日：2018-06-12
申请号：US15197451
申请日：2016-06-29
Applicant: General Electric Company
Inventor： Thomas Lee Becker , Brandon Wayne Miller , Daniel Alan Niergarth , Bugra Han Ertas
CPC classification number: F01D25/164 , F01D9/023 , F01D25/22 , F02C7/06 , F02C9/18 , F05D2220/32 , F05D2240/50 , F05D2240/53 , F05D2240/54 , F16C32/0603 , F16C32/0614 , F16C2360/23 , F23R3/283
Abstract: A bearing assembly for a turbine engine includes a first gas bearing configured to receive a load from a rotating shaft of the turbine engine, a transmission disk configured to receive the load from the first gas bearing, and a damping member coupled to a casing of a combustor section of the turbine engine. The transmission disk includes a gas delivery disk, which includes an axial opening configured to facilitate an axial flow through the gas delivery disk and a duct configured to facilitate a radial flow through the gas delivery disk to form the first gas bearing. The damping member is configured to receive the load from the transmission disk.
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公开(公告)号：US20180057182A1
公开(公告)日：2018-03-01
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
CPC classification number: B64D29/04 , B64C1/16 , B64C21/06 , B64D27/20 , B64D33/02 , B64D2033/0226 , Y02T50/166
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：US09637217B2
公开(公告)日：2017-05-02
申请号：US14859549
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: B64C1/16 , B64C21/06 , B64C2230/00 , B64D27/14 , B64D27/20 , B64D29/00 , B64D29/04 , B64D33/02 , F02K3/04 , F05D2220/76 , Y02T50/166
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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Patent Agency Ranking
公开(公告)号：US20240117770A1
公开(公告)日：2024-04-11
申请号：US18486523
申请日：2023-10-13
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：US11802492B2
公开(公告)日：2023-10-31
申请号：US17749805
申请日：2022-05-20
Applicant: General Electric Company
Inventor： Paul Robert Gemin , Thomas Lee Becker , Tod Robert Steen
CPC classification number: F01D25/04 , F01D15/10 , F02C3/04 , F02C6/14 , F02C7/22 , F05D2220/32 , F05D2240/35 , F05D2260/96 , H02K7/003 , H02K7/1823
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：US20230160346A1
公开(公告)日：2023-05-25
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 , F05D2300/603 , F05D2240/54 , F05D2250/711 , F05D2240/61
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：US20220373019A1
公开(公告)日：2022-11-24
申请号：US17328800
申请日：2021-05-24
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
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：US20220372917A1
公开(公告)日：2022-11-24
申请号：US17328795
申请日：2021-05-24
Applicant: General Electric Company
Inventor： Narayanan Payyoor , Weize Kang , Thomas Lee Becker , Richard Schmidt
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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