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公开(公告)号：US20240328324A1
公开(公告)日：2024-10-03
申请号：US18621779
申请日：2024-03-29
Applicant: General Electric Company
Inventor： Ning Fang , William Bowden , Weili Yang , Keith E. Blodgett , Guohua Zhong , Niloufar Hosseiny
CPC classification number: F01D11/005 , F01D25/24 , F05D2220/323 , F05D2240/56
Abstract: Apparatus are disclosed for a turbofan comprising: a bifurcation including a first track; and an outer casing including an airflow inlet and an airflow outlet, the outer casing adjustable into a closed position and an open position, the outer casing positioned around the bifurcation, the outer casing including a first slider for movement between the closed position and the open position that mates with the first track, the first track including a brush seal holder and a brush seal including a plurality of bristles having a compressed state in the closed position and a decompressed state in the open position.
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公开(公告)号：US20190186598A1
公开(公告)日：2019-06-20
申请号：US16284358
申请日：2019-02-25
Applicant: General Electric Company
Inventor： Kennneth Lee Fisher , Darren Lee Hallman , Bugra Han Ertas , Donald Albert Bradley , Haris Ligata , William Howard Hasting , Ning Fang , Gert Johannes van der Merwe , Mark Alan Rhoads
CPC classification number: F16H1/2809 , F02C7/36 , F16C19/361 , F16H57/082
Abstract: A planet gear includes an annular planet gear rim having a constant inner radius along a complete axial length and an outer radius defined as the radial distance to the root of the gear teeth. The annular planet gear rim further has an average rim radius defined at a halfway point between the constant inner radius and the outer radius. The average rim radius and the rim thickness define a ratio including values in a range from and including about 4 to and including about 9. A gear assembly and turbomachine including the planet gear are disclosed.
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公开(公告)号：US20170191548A1
公开(公告)日：2017-07-06
申请号：US14984472
申请日：2015-12-30
Applicant: General Electric Company
Inventor： Kenneth Lee Fisher , Darren Lee Hallman , Bugra Han Ertas , Donald Albert Bradley , Haris Ligata , William Howard Hasting , Ning Fang , Gert Johannes van der Merwe , Mark Alan Rhoads
CPC classification number: F16H57/08 , F02C7/36 , F02K3/06 , F05D2260/40311
Abstract: A planet gear includes an annular planet gear ring including an annular planet gear rim. The annular planet gear rim has an inner radius and an outer radius. The inner radius and the outer radius define a rim thickness therebetween. The annular planet gear rim further has a bending stress neutral axis. The bending stress neutral axis radius and the rim thickness define a ratio including values in a range from and including about 3 to and including about 10.
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公开(公告)号：US20170159564A1
公开(公告)日：2017-06-08
申请号：US14962313
申请日：2015-12-08
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
CPC classification number: F02C7/14 , B64D37/34 , F01D25/18 , F02C7/06 , F02C7/224 , F05D2240/40 , F05D2260/213 , Y02T50/675
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US20170096941A1
公开(公告)日：2017-04-06
申请号：US14876124
申请日：2015-10-06
Applicant: General Electric Company
Inventor： Randy Thomas Antelo , Gert J. van der Merwe , Ning Fang , Steve D. Miller
CPC classification number: F02C7/36 , F01D25/04 , F02C3/04 , F02C3/107 , F05D2220/32 , F05D2240/60 , F05D2240/62 , F05D2260/4031 , F05D2260/96 , F05D2300/501 , F16C1/02 , F16C2360/23 , F16D3/50 , F16D3/72
Abstract: A gas turbine gearbox input shaft including a gear coupling engaged with an engine power gearbox and extending along a central engine axis thereof. The shaft may include a separable tuning segment coaxially joined to the gear coupling, and a spool coupling joined to the separable tuning segment opposite of the gear coupling, the spool coupling being engaged with an engine turbine spool. Methods of using the input shaft are also provided.
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Patent Agency Ranking
公开(公告)号：US20190153954A1
公开(公告)日：2019-05-23
申请号：US16256629
申请日：2019-01-24
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US10215097B2
公开(公告)日：2019-02-26
申请号：US15041224
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US20170159569A1
公开(公告)日：2017-06-08
申请号：US15041224
申请日：2016-02-11
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
CPC classification number: F02C7/224 , B64D27/12 , B64D37/02 , B64D37/34 , F02C7/06 , F02C7/14 , F02C7/236 , F05D2220/32 , F05D2220/764 , F05D2240/35 , F05D2260/20 , F05D2260/205 , F05D2260/213 , F05D2260/98 , Y02T50/675
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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公开(公告)号：US20170159493A1
公开(公告)日：2017-06-08
申请号：US14962217
申请日：2015-12-08
Applicant: General Electric Company
Inventor： Kyle Robert Snow , Brandon Wayne Miller , Duane Howard Anstead , Jonothan Allen Scheetz , Mohammed El Hacin Sennoun , Ning Fang
CPC classification number: F01D25/18 , F01D25/16 , F02C3/04 , F02C7/06 , F05D2240/50 , F05D2260/6022 , F05D2260/98
Abstract: A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0° F. and about 550° F.
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公开(公告)号：US11098647B2
公开(公告)日：2021-08-24
申请号：US16256629
申请日：2019-01-24
Applicant: General Electric Company
Inventor： Brandon Wayne Miller , Duane Howard Anstead , Mohammed El Hacin Sennoun , Ning Fang , Kyle Robert Snow
Abstract: A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500° F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.
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