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公开(公告)号：US12092031B2
公开(公告)日：2024-09-17
申请号：US17246382
申请日：2021-04-30
Applicant: Pratt & Whitney Canada Corp.
Inventor： Eric Durocher
CPC classification number: F02C7/222 , B64D37/32 , F02C7/25 , F02C3/22 , F05D2220/323 , F05D2240/35 , F05D2260/60 , F05D2260/605
Abstract: In accordance with at least one aspect of the present disclosure, there is provided a fuel system of an aircraft engine, comprising: a fuel conduit interface connecting a fuel conduit to a component of the fuel system; and a sweep line structure. The sweep line structure includes an inner surface facing toward, extending around, and defining a cavity around the fuel conduit interface, and an outer surface opposite the inner surface, the cavity being fluidly sealed relative to the outer surface.
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102.发明公开
公开(公告)号：US20240218805A1
公开(公告)日：2024-07-04
申请号：US18091919
申请日：2022-12-30
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Ryan Humes , Andrew Eifert , Paulo Bazan
CPC classification number: F01D17/162 , F02C9/22 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2260/60
Abstract: A vane adjustment assembly includes a plurality of vanes, an annular ring coupled to the vanes, and a ring adjustment plate. The adjustment plate includes a main plate portion arranged on the ring and including a first adjustment region defined between two walls and a first elongated opening formed through the first adjustment region, and an adjustment fastener removably arranged in the first adjustment region between the first and second walls and including an adjustment head and a fastening pin eccentrically coupled to the adjustment head and removably coupled to the annular ring. The adjustment fastener can be selectively arranged at rotational positions within the first adjustment region so as to selectively arrange the fastening pin at distinct circumferential positions relative to the first and second walls such that the main plate portion can be positioned at distinct circumferential positions.
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公开(公告)号：US12025055B1
公开(公告)日：2024-07-02
申请号：US18158690
申请日：2023-01-24
Applicant: General Electric Company
Inventor： Trevor H. Wood , Michael J. McMahon
CPC classification number: F02C7/042 , F02C7/057 , F05D2220/323 , F05D2240/12 , F05D2260/60 , F05D2260/96
Abstract: A turboprop engine includes a main nacelle body, a rotatable hub provided on the main nacelle body, a plurality of propellers connected to the rotatable hub, and a nacelle extension coupled to the main nacelle body, the nacelle extension including at least one wall defining an air intake inlet. The air intake inlet is movable in an airflow axis with respect to a trailing edge of a propeller in the plurality of propellers to vary a distance between the air intake inlet and the trailing edge of the propeller during various phases of operation of the turboprop engine.
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公开(公告)号：US11988101B2
公开(公告)日：2024-05-21
申请号：US18155934
申请日：2023-01-18
Applicant: General Electric Company
Inventor： Laurie Ann Cribley , Rubi Elizabeth Triana Zorsano
IPC: F01D17/16
CPC classification number: F01D17/162 , F05D2220/30 , F05D2240/12 , F05D2260/60
Abstract: A device for fixing the position of adjustable vane rows of a turbomachine is disclosed. The device is intended for use with a turbomachine in which the guide vanes of a row of adjustable guide vanes are coupled together by a synchronizing ring. The device includes a support arm and at least one ring fixing set including a holding member and a fixing bolt. The fixing bolt is provided and dimensioned to engage an opening at the circumference of the synchronizing ring and to fix the position of the synchronizing ring and thus of the adjustable guide vanes coupled to the synchronizing ring.
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公开(公告)号：US20240151149A1
公开(公告)日：2024-05-09
申请号：US18549415
申请日：2022-03-15
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Paul Ghislain Albert LEVISSE , Caroline Marie FRANTZ , Didier Gabriel Bertrand DESOMBRE , Christophe Marcel Lucien PERDRIGEON , Jean-Claude Christian TAILLANT
CPC classification number: F01D7/02 , F01D25/16 , F05D2220/323 , F05D2240/30 , F05D2260/60
Abstract: A fan module for an aircraft turbine engine, the module including a fan having variable-pitch blades and an oil transfer device for transferring oil between a stator and a rotor, the device including a stator ring having a cylindrical inner surface and internal oil ducts and a shaft engaged in the ring and having a cylindrical outer surface and internal oil ducts; the device includes a plain bearing located between said cylindrical inner surface and the cylindrical outer surface and defined by a single band; and rolling bearings mounted between the ring and the shaft, on either side of the plain bearing, each of these rolling bearings having one of the rings thereof integrated in one of the elements selected from the ring and the shaft.
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106.发明公开
公开(公告)号：US20240076991A1
公开(公告)日：2024-03-07
申请号：US18505595
申请日：2023-11-09
Inventor： Ryan C. Humes
CPC classification number: F01D9/023 , F01D17/145 , F23R3/002 , F05D2240/35 , F05D2260/232 , F05D2260/60 , F23R2900/03043
Abstract: A gas turbine engine comprises a turbine, a combustor fluidly coupled to the turbine, and a cooling air system. The turbine includes including a turbine rotor having a shaft mounted for rotation about an axis of the gas turbine engine and a set of turbine blades coupled to the turbine rotor for rotation therewith. The combustor includes an outer combustor case and an inner combustor case that cooperate to define a combustion chamber. The cooling air system is configured to cool the turbine using air form the combustion chamber of the combustor.
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公开(公告)号：US11920482B2
公开(公告)日：2024-03-05
申请号：US18155942
申请日：2023-01-18
Applicant: General Electric Company
Inventor： Laurie Ann Cribley , Rubi Elizabeth Triana Zorsano
IPC: F01D17/16
CPC classification number: F01D17/162 , F05D2220/30 , F05D2240/12 , F05D2260/60
Abstract: A device for fixing the position of adjustable vane rows of a turbomachine is provided. The device includes a support arm and at least one clamping tool. The at least one clamping tool is attached to the support arm. The at least one clamping tool includes a clamping head and a retaining element. The retaining element connects the clamping head to the support arm.
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108.发明公开
公开(公告)号：US20240068408A1
公开(公告)日：2024-02-29
申请号：US18224781
申请日：2023-07-21
Applicant: Collins Engine Nozzles, Inc.
Inventor： Brandon P. Williams , Michael Ferrarotti , Murtuza Lokhandwalla , Todd Haugsjaahabink , Russell P. Rourke, Jr. , Jay W. Kokas , Richard E. Versailles
CPC classification number: F02C7/232 , F23R3/346 , F05D2240/35 , F05D2260/60 , F23N2241/20
Abstract: A system includes an injector having a scheduling valve assembly and a nozzle in fluid communication with the valve assembly. The scheduling valve assembly is configured for regulation of flow from an inlet of the injector to the nozzle. The injector includes two fluid circuits between the inlet of the injector and two respective outlets of the nozzle for staged flow output from the nozzle. A first one of the two fluid circuits is a primary circuit, and a second one of the two fluid circuits is a secondary circuit. A solenoid valve is connected in fluid communication with the scheduling valve assembly, wherein the solenoid valve is configured to adjust position of a hydromechanical valve spool of the valve assembly.
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109.发明公开
公开(公告)号：US20230417156A1
公开(公告)日：2023-12-28
申请号：US18034988
申请日：2021-11-10
Applicant: SAFRAN HELICOPTER ENGINES
CPC classification number: F01D17/162 , F04D29/563 , F05D2220/329 , F05D2240/128 , F05D2260/60
Abstract: Device (30) for controlling an airflow guiding system (20), comprising at least one actuator (31) configured to translate a control rod (32) between a first and a second end position of a nominal operating range in which at least one vane (21a) of the airflow guiding system (20) can be moved between a first and a second angle, the control rod (32) being connected to the vane (21a) by a control lever (33) comprising a first control rod (36) and a second control rod (37) which are hinged together. The actuator (31) is configured to bring the control rod (32) into a safety position located beyond the second end position of the nominal operating range and to orient the vane (21a) at a safe pitch angle between the first angle and the second angle.
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110.发明公开
公开(公告)号：US20230407797A1
公开(公告)日：2023-12-21
申请号：US18251290
申请日：2021-11-02
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Eva Julie LEBEAULT , Philippe Gérard CHANEZ
CPC classification number: F02C9/18 , F02C6/08 , F02K1/66 , F02K1/74 , F01D17/12 , F05D2220/323 , F05D2240/128 , F05D2260/60 , F05D2270/051
Abstract: An aircraft dual-flow turbine engine assembly includes: an internal shroud for externally delimiting a primary flow path of the turbine engine gases; an external shroud for internally delimiting a secondary flow path of the turbine engine gas; and at least one air discharge duct extending between the internal shroud and the external shroud, the air discharge duct opening into the secondary flow path through an outlet orifice equipped with discharge fins. At least some of the discharge fins are movably mounted so as to be able to be incidence-control between a propulsion position, and a reverse thrust position.
