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公开(公告)号：US12234748B2
公开(公告)日：2025-02-25
申请号：US18334799
申请日：2023-06-14
Inventor： Eyitayo James Owoeye , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals: [ HTSA OGV × BPR ( BPR + 1 ) × C a i r × ( T i n l e t - T a i r ) × v f l i g h t × D f a n F n T o t a l × v tip speed × Δ H ] 1 / 3 , and wherein HTSA OGV = N v a n e × D fan 2 × ( 1 - R OGV _ ratio 2 ) 2 × sin ( 180 / N v a n e ) × sin θ OGV × f OGV .
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公开(公告)号：US20250052194A1
公开(公告)日：2025-02-13
申请号：US18925935
申请日：2024-10-24
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
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公开(公告)号：US12188414B2
公开(公告)日：2025-01-07
申请号：US18307938
申请日：2023-04-27
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and thereby form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.
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公开(公告)号：US20240418094A1
公开(公告)日：2024-12-19
申请号：US18334799
申请日：2023-06-14
Inventor： Eyitayo James Owoeye , Ravindra Shankar Ganiger , Adam Tomasz Pazinski
Abstract: A gas turbine engine is provided having a plurality of outlet guide vanes, each defining an internal thermal fluid passageway. The engine defining an Outlet Guide Vane Cooling Capacity greater than 0.01 and less than 13, wherein OGVCC equals: [ HTSA OGV × BPR ( BPR + 1 ) × C air × ( T inlet - T air ) × v flight × D fan Fn Total × v tip speed × Δ H ] 1 / 3 , and wherein HTSA OGV = N vane × D fan 2 × ( 1 - R OGV _ ratio 2 ) 2 × sin ( 180 / N vane ) × sin θ OGV × f OGV .
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公开(公告)号：US12123324B2
公开(公告)日：2024-10-22
申请号：US18343013
申请日：2023-06-28
Inventor： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC: F01D9/02
CPC classification number: F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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Patent Agency Ranking
36.发明公开公开(公告)号：US20240167422A1
公开(公告)日：2024-05-23
申请号：US18378974
申请日：2023-10-11
Inventor： Adam Tomasz Pazinski , Miroslaw Sobaniec , Christopher N. Delametter
CPC classification number: F02C7/18 , F02C6/00 , F05D2220/76
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine. The first cooling airflow path is in communication with a second cooling airflow path located outside the enclosure that at least partially defines a second cooling airflow buffer cavity at least partially around the enclosure. A cooling duct provides pressurized air to the first cooling airflow path such that the air flows along both the first cooling airflow path and the second cooling airflow path providing the first cooling airflow buffer cavity and the second cooling airflow buffer cavity.
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公开(公告)号：US20240051656A1
公开(公告)日：2024-02-15
申请号：US18085112
申请日：2022-12-20
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
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38.发明授权公开(公告)号：US11891954B2
公开(公告)日：2024-02-06
申请号：US17400936
申请日：2021-08-12
Inventor： Adam Tomasz Paziński , Miroslaw Sobaniec , Christopher N. Delametter
CPC classification number: F02C7/18 , F02C6/00 , F05D2220/76
Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine. A compressor section and a turbine section are arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An electrical machine is coupled to the rotary member and is located at least partially inward of the core airflow path in a radial direction. An enclosure at least partially encloses the electrical machine. The enclosure at least partially defines a first cooling airflow path within the enclosure that at least partially defines a first cooling airflow buffer cavity at least partially around the electrical machine. The first cooling airflow path is in communication with a second cooling airflow path located outside the enclosure that at least partially defines a second cooling airflow buffer cavity at least partially around the enclosure. A cooling duct provides pressurized air to the first cooling airflow path such that the air flows along both the first cooling airflow path and the second cooling airflow path providing the first cooling airflow buffer cavity and the second cooling airflow buffer cavity.
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公开(公告)号：US11814988B2
公开(公告)日：2023-11-14
申请号：US17475585
申请日：2021-09-15
Inventor： Rodrigo Rodriguez Erdmenger , Rudolph Selmeier , Mehdi Milani Baladi , Jacek Marian Elszkowski
CPC classification number: F01D9/041 , F01D9/045 , F01D17/105 , F05D2240/12 , F05D2260/606
Abstract: A turbomachine defining a flowpath therethrough at which a fluid is compressed is provided, in which the turbomachine includes a first compressor in serial flow arrangement upstream of a second compressor. The second compressor includes a port at the flowpath and is configured to receive at least a portion of the fluid from the flowpath from the second compressor. The first compressor includes a vane positioned at the flowpath and the vane includes an opening at the flowpath configured to egress the portion of the fluid from the port into the flowpath.
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公开(公告)号：US11788425B2
公开(公告)日：2023-10-17
申请号：US17561156
申请日：2021-12-23
Applicant: General Electric Company , General Electric Deutschland Holding GmbH , General Electric Company Polska Sp. z o.o.
Inventor： Ashish Sharma , Piotr Jerzy Kulinski , Adam Tomasz Pazinski , Tomasz Jan Bulsiewicz , Scott Alan Schimmels
CPC classification number: F01D11/18 , F01D9/04 , F01D11/24 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2260/201
Abstract: A gas turbine engine including: a first turbine rotor assembly including a plurality of first turbine rotor blades extended within a gas flowpath; and a casing surrounding the first turbine rotor assembly, wherein the casing comprises an outer casing wall extended around the first turbine rotor assembly; a plurality of vanes extended from the outer casing wall and within the gas flowpath at a location aft of the first turbine rotor assembly; and a thermal control ring positioned outward along a radial direction from the outer casing wall, and wherein the thermal control ring comprises a body and a plurality of pins, and wherein the plurality of pins extend between the outer casing wall and the body.
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