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公开(公告)号：US12227284B2
公开(公告)日：2025-02-18
申请号：US18415155
申请日：2024-01-17
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Krzysztof Jedliński , Mirosław Sobaniec , Mateusz Gołdyn , Tomasz Biwański , Tomasz Kosieradzki , Dariusz Łodkowski
Abstract: A pitch change mechanism for an aircraft engine includes a unison ring, a plurality of crankshafts coupled to the unison ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the unison ring, and an actuator cylinder and an actuator piston. The actuator cylinder is coupled to the inner shaft and is configured to move relative to the actuator piston along a longitudinal axis of the pitch change mechanism. Movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around a longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.
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公开(公告)号：US20250052193A1
公开(公告)日：2025-02-13
申请号：US18925916
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 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：US20250019065A1
公开(公告)日：2025-01-16
申请号：US18415155
申请日：2024-01-17
Applicant: General Electric Company Polska sp. z o.o.
Inventor： Krzysztof Jedlinski , Miroslaw Sobaniec , Mateusz Goldyn , Tomasz Biwanski , Tomasz Kosieradzki , Dariusz Lodkowski
Abstract: A pitch change mechanism for an aircraft engine includes a unison ring, a plurality of crankshafts coupled to the unison ring and configured to receive a plurality of blades, an inner shaft coupled to the plurality of crankshafts and the unison ring, and an actuator cylinder and an actuator piston. The actuator cylinder is coupled to the inner shaft and is configured to move relative to the actuator piston along a longitudinal axis of the pitch change mechanism. Movement of the actuator cylinder relative to the actuator piston is transferred to a rotation of each of the plurality of crankshafts around a longitudinal axis of each of the plurality of crankshafts to change a pitch of the plurality of blades.
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公开(公告)号：US12140040B2
公开(公告)日：2024-11-12
申请号：US17839859
申请日：2022-06-14
Abstract: An airfoil assembly for a gas turbine engine includes: an inner support structure configured to circumscribe a longitudinal axis of the gas turbine engine; an outer support structure configured to circumscribe the longitudinal axis of the gas turbine engine, the outer support structure circumscribing the inner support structure; and a stage including a plurality of airfoils extending from the inner support structure towards the outer support structure, the plurality of airfoils including: a first airfoil defining a first sweep angle, a first axial position, and a first lean angle; and a second airfoil defining a second sweep angle, a second axial position, and a second lean angle, wherein the second sweep angle is different than the first sweep angle, the second axial position is different than the first axial position, the second lean angle is different than the first lean angle, or a combination thereof.
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公开(公告)号：US20240369073A1
公开(公告)日：2024-11-07
申请号：US18354005
申请日：2023-07-18
Applicant: General Electric Company Polska Sp. z o.o.
Inventor： Dariusz Olczak , Maciej Stanczyk , Damian Owczarek , Adam Tomasz Pazinski
Abstract: An inlet guide vane for use in a gas turbine engine may include an internal cavity for receipt of an anti-ice air to discourage build-up of ice in a flow path of the gas turbine engine. The inlet guide vane can include an anti-ice flow passage formed in a tip of the inlet guide vane which receives the anti-ice air from the internal cavity prior to being discharged from the inlet guide vane. Anti-ice air can be discharged through a tip of the inlet guide vane, through a leading edge of the inlet guide vane, or into a shaft side passage provided in a component defining the inner flow surface. In another form, anti-ice air can be provided from a sump of the gas turbine engine, through a shaft side passage, and into the inlet guide vane before being discharged.
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Patent Agency Ranking
公开(公告)号：US20240280053A1
公开(公告)日：2024-08-22
申请号：US18307938
申请日：2023-04-27
Inventor： Arthur William Sibbach , Adam Tomasz Pazinski
CPC classification number: F02C7/18 , F01D17/12 , F02C7/04 , F05D2260/201 , F05D2260/232
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：US20240239506A1
公开(公告)日：2024-07-18
申请号：US18316577
申请日：2023-05-12
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a lengthwise direction and comprising a leading edge section, the leading edge section defining a leading edge camber that varies along the lengthwise direction of the pylon fairing.
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公开(公告)号：US20240239505A1
公开(公告)日：2024-07-18
申请号：US18307917
申请日：2023-04-27
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan that defines a plurality of fan wakes; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a pylon fairing dihedral, wherein the pylon fairing dihedral is in a direction opposite the incoming fan flow swirl and associated sheared profiles of fan wakes upon arrival at the pylon leading edge.
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公开(公告)号：US20240239503A1
公开(公告)日：2024-07-18
申请号：US18307110
申请日：2023-04-26
Inventor： William Joseph Bowden , Lukasz Ignacy Mazurkiewicz , Syed Arif Khalid , Trevor Howard Wood
Abstract: An aircraft defining a longitudinal centerline and extending between a forward end and an aft end is provided. The aircraft comprises a fuselage extending between the forward end of the aircraft and the aft end of the aircraft; a wing assembly extending laterally outwardly with respect to the longitudinal centerline from a portion of the fuselage; an unducted turbofan engine including an unducted fan defining a fan diameter; and a pylon fairing that connects the unducted turbofan engine to the wing assembly, the pylon fairing defining a leading edge and including a first inflection point along the leading edge, the first inflection point defining a first radius of curvature that is less than 5 times the fan diameter and greater than 0.1 times the fan diameter.
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公开(公告)号：US11901799B2
公开(公告)日：2024-02-13
申请号：US17170221
申请日：2021-02-08
Applicant: General Electric Company , General Electric Company Polska sp. z o.o. , General Electric Deutschland Holding GmbH
Inventor： Miroslaw Czarnik , Adam Tomasz Paziński , Bartłomiej Drozd , Darek Zatorski , Maciej Krzysztof Grunwald , Mohamed Osama , John R. Yagielski
CPC classification number: H02K7/1815 , H02K1/12 , H02K7/003 , H02K7/08 , H02K7/14
Abstract: An electrical machine includes a stator assembly coupled to an engine stator component of a propulsion engine. The stator assembly includes a stator support assembly fixedly attached to the engine stator component and a stator disposed on a supporting surface of the stator support structure. The electrical machine also includes a rotor assembly including a rotor support structure connected to a shaft of the propulsion engine and a rotor attached to the rotor support structure such that the rotor is disposed radially inward of the stator. The rotor exchanges rotational energy with the shaft to operate as either an electrical motor or an electrical generator.
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