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公开(公告)号：US11339723B2
公开(公告)日：2022-05-24
申请号：US14431839
申请日：2013-03-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Frederick M. Schwarz , William G. Sheridan , Glenn Levasseur
Abstract: A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.
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公开(公告)号：US11597527B2
公开(公告)日：2023-03-07
申请号：US17376675
申请日：2021-07-15
Applicant: Raytheon Technologies Corporation
IPC: F02C6/14 , B64D27/24 , B64D27/10 , F01D15/10 , F02C7/36 , H02K7/18 , B64D27/02 , F02C6/02 , F02C3/107
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US11091272B2
公开(公告)日：2021-08-17
申请号：US16039849
申请日：2018-07-19
Applicant: Raytheon Technologies Corporation
IPC: F02C6/14 , B64D27/24 , B64D27/10 , F01D15/10 , F02C7/36 , H02K7/18 , B64D27/02 , F02C6/02 , F02C3/107
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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Patent Agency Ranking
公开(公告)号：US11781490B2
公开(公告)日：2023-10-10
申请号：US17579938
申请日：2022-01-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , Gabriel L. Suciu , Gary M. Stetson
CPC classification number: F02C7/36 , F01D17/162 , F02C3/064 , F02C7/32 , F02C9/20 , F05D2220/32 , F05D2260/4031
Abstract: A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.
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公开(公告)号：US20230182909A1
公开(公告)日：2023-06-15
申请号：US18103935
申请日：2023-01-31
Applicant: Raytheon Technologies Corporation
CPC classification number: B64D27/24 , B64D27/10 , F01D15/10 , F02C6/14 , F02C7/36 , H02K7/1823 , F05D2270/053 , B64D2221/00 , F02C3/107
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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公开(公告)号：US11691388B2
公开(公告)日：2023-07-04
申请号：US14903913
申请日：2014-07-09
Applicant: Raytheon Technologies Corporation
Inventor： Glenn Levasseur , Shari L. Bugaj , Grant O. Cook, III
IPC: C25D1/10 , B32B15/08 , C25D5/02 , C25D7/04 , C23C18/16 , B29B11/06 , B29B11/14 , B29C43/18 , B29C45/14 , C23C26/00 , E04B1/19 , E04B1/30 , B29K101/10 , B29K101/12 , B29K105/20 , B29K705/00 , B29L9/00
CPC classification number: B32B15/08 , B29B11/06 , B29B11/14 , B29C43/183 , B29C45/14 , C23C18/1605 , C23C26/00 , C25D5/022 , C25D7/04 , E04B1/19 , E04B1/30 , B29K2101/10 , B29K2101/12 , B29K2105/20 , B29K2705/00 , B29L2009/00 , B32B2250/02 , B32B2307/558 , B32B2605/00 , E04B2001/1927
Abstract: An encapsulated polymeric article is disclosed. The encapsulated polymeric article may include a polymer substrate and a metallic outer shell at least partially encapsulating the polymer substrate. The encapsulated polymeric article may be fabricated by a method comprising: 1) providing a mandrel in a shape of the encapsulated polymeric article, 2) shaping the metallic outer shell on the mandrel, 3) removing the mandrel from the metallic outer shell, and 4) molding the polymeric substrate into the metallic outer shell through a port formed in the metallic outer shell to provide the encapsulated polymeric article.
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公开(公告)号：US20220145807A1
公开(公告)日：2022-05-12
申请号：US17579938
申请日：2022-01-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Glenn Levasseur , Gabriel L. Suciu , Gary M. Stetson
Abstract: A gas turbine engine includes a propulsor having a plurality of blades, a compressor section including a first compressor and a second compressor aft of the first compressor. The first compressor includes at least one array of first variable guide vanes that control operation of the first compressor. The second compressor includes at least one array of second variable guide vanes that control operation of the second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture is driven by the second turbine for rotating the propulsor.
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公开(公告)号：US20210339880A1
公开(公告)日：2021-11-04
申请号：US17376675
申请日：2021-07-15
Applicant: Raytheon Technologies Corporation
Abstract: An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.
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