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公开(公告)号：US20250084771A1
公开(公告)日：2025-03-13
申请号：US18492837
申请日：2023-10-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
IPC: F01D17/16
Abstract: A turbine engine comprising a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement and defining a stator portion and a rotor portion, which rotates about an engine centerline. The rotor portion comprising a variable pitch airfoil assembly. The variable pitch airfoil assembly having an airfoil and a balancing insert.
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公开(公告)号：US11674399B2
公开(公告)日：2023-06-13
申请号：US17368961
申请日：2021-07-07
Applicant: General Electric Company
Inventor： Ravindra Shankar Ganiger , Praveen Sharma , Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
CPC classification number: F01D5/282 , F01D5/147 , F01D5/30 , F05C2251/08 , F05D2240/303 , F05D2240/304 , F05D2240/307 , F05D2300/505
Abstract: An airfoil arrangement for a gas turbine engine may include a support device using a shape memory alloy to support and control the airfoil. The support device may be formed as part of a fan blade. The arrangement may be configured to reduce overall weight and dimensions of the gas turbine engine.
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公开(公告)号：US20230029918A1
公开(公告)日：2023-02-02
申请号：US17490401
申请日：2021-09-30
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
Abstract: An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span. The frangible airfoil portion including a plurality of composite plies and one or more shape memory alloy inserts disposed between the plurality of composite plies. A gas turbine engine including a frangible airfoil and methods for forming a frangible airfoil are also disclosed.
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公开(公告)号：US11261753B2
公开(公告)日：2022-03-01
申请号：US15832814
申请日：2017-12-06
Applicant: General Electric Company
Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.
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公开(公告)号：US11156099B2
公开(公告)日：2021-10-26
申请号：US15471729
申请日：2017-03-28
Applicant: General Electric Company
Inventor： Nitesh Jain , Abhijeet Jayshingrao Yadav , Kishore Budumuru , Nicholas Joseph Kray
Abstract: A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge.
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Patent Agency Ranking
公开(公告)号：US20250059894A1
公开(公告)日：2025-02-20
申请号：US18476474
申请日：2023-09-28
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Abhijeet Jayshingrao Yadav , Frank Worthoff , Nicholas Joseph Kray , Nitesh Jain , Balaraju Suresh
Abstract: A turbine engine including a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The turbine engine further including a composite airfoil assembly. The composite airfoil assembly having an outer wall, a composite body at least partially defining the outer wall, and a tip cap at least partially defining the outer wall.
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公开(公告)号：US11773732B2
公开(公告)日：2023-10-03
申请号：US17236257
申请日：2021-04-21
Applicant: General Electric Company
Inventor： Nitesh Jain , Nicholas Joseph Kray , Abhijeet Jayshingrao Yadav
CPC classification number: F01D5/282 , F01D5/147 , F02C7/24 , F05D2240/30 , F05D2260/96 , F05D2300/44 , F05D2300/603 , F05D2300/614
Abstract: A component for a turbine engine is provided. The component includes a main body portion having a flow path surface; and a protective layer formed of a chopped fiber material, the protective layer cohered to at least a portion of the flow path surface of the main body portion.
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公开(公告)号：US20220212772A1
公开(公告)日：2022-07-07
申请号：US17141899
申请日：2021-01-05
Applicant: General Electric Company
Inventor： Nicholas J. Kray , Nitesh Jain , Abhijeet Jayshingrao Yadav
Abstract: Airframe localized keel structures are disclosed. An example aircraft includes an airframe, a first engine mounted on a first side of the airframe, a second engine mounted on a second side of the airframe, and an airframe keel positioned on at least one of a lower portion of the airframe or an upper portion of the airframe between the first engine and the second engine, the airframe keel to prevent an object from exiting the first engine and impacting the second engine.
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公开(公告)号：US20190170012A1
公开(公告)日：2019-06-06
申请号：US15832814
申请日：2017-12-06
Applicant: General Electric Company
Abstract: A rotor assembly includes a fan rotor shaft coupled to a fan rotor, a low pressure turbine rotor shaft coupled to a low pressure turbine rotor, and a joint device configured to connect the fan rotor shaft to the low pressure turbine rotor shaft, to allow torsion, shear and bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under normal operation, and allow torsion and shear but prevent bending to be transferred between the fan rotor shaft and the low pressure turbine rotor shaft under a fan blade-out event.
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公开(公告)号：US20180283180A1
公开(公告)日：2018-10-04
申请号：US15471729
申请日：2017-03-28
Applicant: General Electric Company
Inventor： Nitesh Jain , Abhijeet Jayshingrao Yadav , Kishore Budumuru , Nicholas Joseph Kray
Abstract: A turbine engine can comprise a fan section, compressor section, a combustion section, and a turbine section in axial flow arrangement. At least one of the fan section and compressor section can include an airfoil with a leading edge, and a plurality of riblets can be arranged on the leading edge.
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