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公开(公告)号：US11624315B2
公开(公告)日：2023-04-11
申请号：US17106252
申请日：2020-11-30
申请人： BorgWarner Inc.
摘要： The disclosure relates to a valve assembly 10 for controlling a volute connecting opening 324 of a multi-channel turbine 500. The valve assembly 10 comprises a housing portion 300, a valve body 100 and an internal lever 200. The housing portion 300 defines a first volute channel 312, a second volute channel 314 and a volute connecting region 320. The housing portion 300 further comprises a cavity 340. The cavity 340 is separated from the volutes 312, 314 and can be accessed from outside the housing portion 300 via a housing opening 342 which extends from outside the housing portion 300 into the cavity 340. The volute connection region 320 is located between the first volute channel 312 and the second volute channel 314 and defines a volute connecting opening 324. The valve body 100 is inserted in the cavity 340 of the housing portion 300 and comprises at least one fin 120. The internal lever 200 is coupled with the valve body 100 and configured to pivotably move the valve body 100 between a first position and a second position. In the first position of the valve body 100, the fin 120 blocks the volute connecting opening 324.
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2.发明授权公开(公告)号：US11598220B2
公开(公告)日：2023-03-07
申请号：US16443245
申请日：2019-06-17
摘要： A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.
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公开(公告)号：US11492921B2
公开(公告)日：2022-11-08
申请号：US16790064
申请日：2020-02-13
IPC分类号： F01D15/10 , F16K39/02 , F01D17/10 , F16K1/12 , F01D17/14 , F01D17/00 , F01D25/00 , F16K25/00 , F16K25/04
摘要： A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.
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公开(公告)号：US11486265B1
公开(公告)日：2022-11-01
申请号：US17383713
申请日：2021-07-23
发明人： Daniel Coutu
IPC分类号： F01D17/16 , F01D9/04 , F01D17/14 , F01D11/00 , B64C27/12 , B64C27/02 , B64C27/04 , B64C27/08
摘要： A variable guide vane assembly has: variable guide vanes having airfoils extending from inner ends to outer ends, the variable guide vanes pivotable about respective spanwise axes between one or more open positions and a closed position, in the closed position, trailing edge regions of the airfoils sealingly engage leading edge regions of adjacent ones of the airfoils to block an air flow; an outer wall extending around the central axis, the outer ends of the variable guide vanes pivotably engaged to the outer wall; and an inner wall extending around the central axis, the inner ends of the variable guide vanes pivotably engaged to the inner wall, the inner wall defining inner faces distributed about the central axis, a shape of the inner faces complementary to a shape of the inner ends of the airfoils to form a seal when the variable guide vanes are in the closed position.
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公开(公告)号：US11480111B2
公开(公告)日：2022-10-25
申请号：US16412771
申请日：2019-05-15
摘要： A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.
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公开(公告)号：US11466599B2
公开(公告)日：2022-10-11
申请号：US16014252
申请日：2018-06-21
发明人： Jérôme Rigouste
IPC分类号： F01M1/10 , F16K17/04 , F01M1/16 , F16K11/10 , F01D17/10 , F02C7/14 , F01D25/18 , F02C7/06 , F01D17/14 , F01D17/06
摘要： A non-return valve with twin plugs is connected to a fluid reservoir and equipment that can receive a small overflow quantity essentially in the gaseous state from the reservoir. This occurs when the primary valve is open. In the case of a larger overflow essentially in the liquid state, the openings are switched over to evacuate the overflow to another outlet branch of the non-return valve, without it being transferred to the equipment. The invention is useful in an oil lubrication circuit, in which a hypothetical fuel leak into the oil could cause the oil reservoir to overflow into the non-return valve and in which a significant flow of liquid to the equipment must be avoided; oil outlet through the other branch of the outlet can remain in a reservoir provided with a drain system.
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公开(公告)号：US11435079B2
公开(公告)日：2022-09-06
申请号：US16440213
申请日：2019-06-13
发明人： Hien Duong
摘要： A compressor diffuser for a gas turbine engine includes diffuser pipes having a tubular body including a generally radial portion, a bend portion and a generally axial portion. The generally axial portion has an exit segment extending parallel to the center axis and terminating at a pipe outlet. The bend portion is disposed radially further from the center axis than the exit segment.
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公开(公告)号：US20220275749A1
公开(公告)日：2022-09-01
申请号：US17188323
申请日：2021-03-01
发明人： Ian A. May
摘要： A turbocharger wastegate actuator arm includes a first section made from a rigid composite material, a second section made from a rigid composite material, and a third section made from a flexible polymeric material positioned between and interconnecting the first and second sections and adapted to allow angular deflection of the first section relative to the second section, wherein a longitudinal axis of the first section and a longitudinal axis of the second section define a first angle when the actuator arm is in the first position and the longitudinal axis of the first section and the longitudinal axis of the second section define a second angle when the actuator arm is in the second position, the first angle being greater than the second angle.
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公开(公告)号：US11428152B1
公开(公告)日：2022-08-30
申请号：US17188323
申请日：2021-03-01
发明人： Ian A. May
摘要： A turbocharger wastegate actuator arm includes a first section made from a rigid composite material, a second section made from a rigid composite material, and a third section made from a flexible polymeric material positioned between and interconnecting the first and second sections and adapted to allow angular deflection of the first section relative to the second section, wherein a longitudinal axis of the first section and a longitudinal axis of the second section define a first angle when the actuator arm is in the first position and the longitudinal axis of the first section and the longitudinal axis of the second section define a second angle when the actuator arm is in the second position, the first angle being greater than the second angle.
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公开(公告)号：US11371369B2
公开(公告)日：2022-06-28
申请号：US17055485
申请日：2019-05-15
申请人： Cummins Ltd.
发明人： Matthew William Edwards , Karl Conlon , Simon David Moore , Christopher Parry , Andrew Sullivan , Paul Ghosh , Mark R. Holden , George E. Sandford , Nandakishore Arcot Madhusudan , Stephen David Hughes , Christopher J. Shaw
摘要： A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.
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