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公开(公告)号：US12031453B1
公开(公告)日：2024-07-09
申请号：US18104452
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Abhijeet Jayshingrao Yadav , Balaraju Suresh
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/323 , F05D2230/23 , F05D2250/75 , F05D2300/603
Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.
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公开(公告)号：US20240209737A1
公开(公告)日：2024-06-27
申请号：US18104452
申请日：2023-02-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Nitesh Jain , Abhijeet Jayshingrao Yadav , Balaraju Suresh
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/323 , F05D2230/23 , F05D2250/75 , F05D2300/603
Abstract: A component and blade assembly for a turbine engine, the component having a wall bounding an interior and defining an exterior surface extending radially between a leading edge and a trailing edge to define a chordwise direction, and between a hub and a tip to define a spanwise direction. A metallic spar extending from the hub in the spanwise direction into the interior, the metallic spar defining a socket. A composite spar extending in the spanwise direction between a spar root and a spar tip, the spar root received in the socket. The component further having a stiffener.
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公开(公告)号：US11970956B2
公开(公告)日：2024-04-30
申请号：US18146511
申请日：2022-12-27
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nitesh Jain , Ricardo Hernandez Pandeli
IPC: F01D7/00
CPC classification number: F01D7/00
Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.
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公开(公告)号：US20200378273A1
公开(公告)日：2020-12-03
申请号：US16424843
申请日：2019-05-29
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nagamohan Govinahalli Prabhakar , Nicholas Joseph Kray , Shivam Mittal , Praveen Sharma , Bhujabal Prashant Mahadeo , Ravindra Shankar Ganiger
Abstract: A composite fan casing for a gas turbine engine defining a central axis is generally provided. The composite fan casing includes a core having a plurality of core layers of reinforcing fibers bonded together with a thermosetting polymeric resin and having an outer surface. The composite fan casing further includes at least one stiffener integrally coupled to an aft portion of the outer surface of the core relative to the central axis. Additionally, the at least one stiffener comprises an elastic material.
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公开(公告)号：US20240271539A1
公开(公告)日：2024-08-15
申请号：US18644467
申请日：2024-04-24
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nitesh Jain , Ricardo Hernandez Pandeli
IPC: F01D7/00
CPC classification number: F01D7/00
Abstract: A gas turbine engine including: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades, the pitch change mechanism including a plurality of linkages, the plurality of linkages including a first linkage coupled to a first fan blade of the plurality of fan blades and a second linkage coupled to a second fan blade of the plurality of fan blades; and a non-uniform blade actuator system operable with one or more of the plurality of linkages to control a pitch of the first fan blade relative to a pitch of the second fan blade.
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Patent Agency Ranking
公开(公告)号：US20240218797A1
公开(公告)日：2024-07-04
申请号：US18317310
申请日：2023-05-15
Applicant: General Electric Company
Inventor： Balaraju Suresh , Guru Venkata Dattu Jonnalagadda , Sandeep Kumar , Nitesh Jain , Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray
IPC: F01D5/28
CPC classification number: F01D5/28 , F05D2220/32 , F05D2230/31 , F05D2300/17
Abstract: Methods of manufacturing airfoil assemblies include forming an airfoil core comprising a foam to define an airfoil shape extending in a first direction and having a pressure side and a suction side extending in a second direction, the second direction being perpendicular to the first direction, between a leading edge and a trailing edge; and electroforming a metal alloy onto an exterior surface of the airfoil core to define an external airfoil shell.
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公开(公告)号：US20240133301A1
公开(公告)日：2024-04-25
申请号：US17970687
申请日：2022-10-20
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nicholas Joseph Kray , Nicholas M. Daggett , Nitesh Jain , Matthew Mark Weaver , Srinivas Addagatla
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/323 , F05D2240/30
Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order. A fan defining a fan axis and comprising a plurality of fan blades is rotatable about the fan axis. A pitch change mechanism is operable with the plurality of fan blades to control a pitch of the plurality of fan blades. A counterweight is connected to each respective fan blade. A spring mechanism is operably associated with each fan blade of the plurality of fan blades to create a spring twisting moment on the respective fan blade that is counter to a centrifugal twisting moment of the respective fan blade.
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公开(公告)号：US11867082B2
公开(公告)日：2024-01-09
申请号：US17236236
申请日：2021-04-21
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray
CPC classification number: F01D5/147 , F01D5/02 , F01D5/28 , F05D2220/32 , F05D2230/80 , F05D2240/307 , F05D2300/17
Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade includes a blade body formed of a first material; and a tip component removably connected to the blade body, the tip component formed of a second material that is different than the first material.
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公开(公告)号：US11668317B2
公开(公告)日：2023-06-06
申请号：US17408986
申请日：2021-08-23
Applicant: General Electric Company
Inventor： Abhijeet Jayshingrao Yadav , Nitesh Jain , Nicholas Joseph Kray , Ravindra Shankar Ganiger , Praveen Sharma
CPC classification number: F04D29/368 , F03G7/0614 , F04D19/002
Abstract: An airfoil arrangement for a gas turbine engine may include a clearance device using a shape memory alloy movable to provide clearance between an airfoil and one or more other components of the gas turbine engine. The clearance 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：US20230008743A1
公开(公告)日：2023-01-12
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
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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