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公开(公告)号：US20230407758A1
公开(公告)日：2023-12-21
申请号：US18452764
申请日：2023-08-21
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
IPC: F01D11/24
CPC classification number: F01D11/24 , F05D2220/32 , F05D2240/55 , F05D2260/213
Abstract: A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.
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公开(公告)号：US20230358144A1
公开(公告)日：2023-11-09
申请号：US18081266
申请日：2022-12-14
Applicant: General Electric Company Polska Sp. z o.o.
Inventor： Tomasz Iglewski
IPC: F01D7/00
CPC classification number: F01D7/00 , F05D2220/36 , F05D2220/32
Abstract: A fan assembly is provided for a gas turbine engine including: a plurality of fan blades, the plurality of fan blades including a first fan blade; and an actuation assembly including: a first linkage connected to the first fan blade; a first pivot point rotatable with the first fan blade, the first linkage further connected to the first pivot point; a control point moveable relative to the first pivot point and connected to the first linkage for changing a relative position of the first fan blade within the plurality of fan blades.
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公开(公告)号：US20230146084A1
公开(公告)日：2023-05-11
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 , F01D25/24 , F05D2220/32
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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公开(公告)号：US20220341346A1
公开(公告)日：2022-10-27
申请号：US17381677
申请日：2021-07-21
Inventor： Miroslaw Czarnik , Adam Tomasz Pazinski , Pawel Zdrojewski , Christopher N. Delametter , Lukasz Maciej Janczak , Maciej Krzysztof Grunwald , Scott Alan Schimmels
Abstract: In one exemplary embodiment, a gas turbine engine is provided. The gas turbine engine defines a radial direction, an axial direction, and an axis extending along the axial direction of the gas. The gas turbine engine includes: a shaft configured to rotate about the axis; an electric machine comprising a rotor coupled to and rotatable with the shaft and a stator, the rotor defining an end along the axial direction; and a cooling manifold rotatable with the rotor and positioned at the end of the rotor, the cooling manifold configured to receive a flow of cooling fluid and provide the cooling fluid to the stator during operation of the gas turbine engine.
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公开(公告)号：US20180215478A1
公开(公告)日：2018-08-02
申请号：US15869823
申请日：2018-01-12
Applicant: General Electric Company Polska sp. z o.o
Inventor： Tomasz IGLEWSKI , Michal FILIPKOWSKI , Aleksander Piotr PASIECZNY
IPC: B64D33/02
CPC classification number: B64D33/02 , B64D2033/022 , B64D2033/0293 , F02C7/055 , F05D2250/10 , F05D2260/607 , Y02T50/675
Abstract: An apparatus for providing foreign object debris protection an air intake of an aircraft engine. The apparatus includes a frame and a plurality of cross-members. The cross-members are positioned in the frame to define a plurality of screen openings. At least one of the cross-members has an aerodynamically efficient cross section.
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Patent Agency Ranking
公开(公告)号：US20250121945A1
公开(公告)日：2025-04-17
申请号：US18990417
申请日：2024-12-20
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 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：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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