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41.发明授权公开(公告)号：US11214381B2
公开(公告)日：2022-01-04
申请号：US15227501
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony Jones , Andre Julien , David Menheere , Jean Thomassin , Richard Ullyott , Daniel Van Den Hende
Abstract: An aircraft heating assembly including an internal combustion engine having a liquid coolant system distinct from any fuel and lubricating system of the engine and including cooling passages in the internal combustion engine for circulating a liquid coolant from a coolant inlet to a coolant outlet, a coolant circulation path outside of the internal combustion engine and in fluid communication with the coolant inlet and the coolant outlet, and a heating element in heat exchange relationship with a portion of the aircraft to be heated. The coolant circulation path extends through a heat exchanger configured to remove a portion of a waste heat from the liquid coolant. The heating element is in heat exchange relationship with the coolant circulation path to receive another portion of the waste heat therefrom. A method of heating a portion of an aircraft is also discussed.
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公开(公告)号：US10550767B2
公开(公告)日：2020-02-04
申请号：US15188277
申请日：2016-06-21
Applicant: Pratt & Whitney Canada Corp.
Inventor： Andreas Eleftheriou , David Menheere , Daniel Alecu
Abstract: A method of installing a segment of a recuperator within an exhaust duct of a gas turbine engine, including positioning the segment such that its exhaust inlet is in fluid flow communication with the turbine section and its exhaust outlet is adapted to deliver an exhaust flow to atmosphere, engaging its air inlet to a plenum in fluid flow communication with the compressor discharge, and engaging its air outlet to another plenum containing the combustor. One of engaging the air inlet and engaging the air outlet includes forming a rigid connection providing sealed fluid flow communication with the corresponding plenum, and the other of engaging the air inlet and engaging the air outlet includes forming a floating connection providing sealed fluid flow communication with the corresponding plenum. The floating connection allows relative movement of the segment within the exhaust duct.
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公开(公告)号：US10450890B2
公开(公告)日：2019-10-22
申请号：US15698905
申请日：2017-09-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Andrew Marshall , Richard A. Kostka
Abstract: A variable stator guide vane system for a gas turbine engine comprises a set of vanes circumferentially distributed around a central axis and rotatably mounted for rotation about respective spanwise axes. A ring gear is rotatably mounted about the central axis. Pinion gears are operatively coupled to respective ones of the vanes and in driving engagement with the ring gear. Biasing members individually bias the pinion gears in meshing engagement with the ring gear.
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公开(公告)号：US10253726B2
公开(公告)日：2019-04-09
申请号：US15227519
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andre Julien , Jean Thomassin , Maxime Courtois , Bruno Villeneuve , Serge Dussault , Richard Ullyott , Serge LaFortune , Luc Dionne , Anthony Jones , Behzad Hagshenas , David Menheere
IPC: F02K1/38 , F01P5/02 , F02B53/02 , F01C21/18 , F02C7/14 , B64D41/00 , F01C1/22 , F02K5/00 , F02C5/00 , F02C7/18 , F02B63/04 , F02B63/06 , F02B67/04 , F01N3/05 , F01P11/10 , F02K1/82 , F02B53/00
Abstract: An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.
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公开(公告)号：US10240522B2
公开(公告)日：2019-03-26
申请号：US15227483
申请日：2016-08-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Anthony Jones , Andre Julien , David Menheere , Jean Thomassin , Richard Ullyott
IPC: F02B63/04 , B64D33/08 , B64D41/00 , F01C1/22 , F02K5/00 , F02C5/00 , F02C7/14 , F02C7/18 , F01P1/06 , F01P5/04 , F01P5/06 , F02B37/00 , F02B53/14 , F02B63/06 , F02B53/02 , F02B67/04 , F01C21/18 , F02B53/00
Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.
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Patent Agency Ranking
公开(公告)号：US09376935B2
公开(公告)日：2016-06-28
申请号：US13717898
申请日：2012-12-18
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andreas Eleftheriou , Denis Leclair , David Denis , David Menheere , Paul Aitchison
CPC classification number: F01D25/162 , F02K3/06 , F05D2230/60 , Y02T50/671 , Y10T29/4932
Abstract: A casing for an aircraft engine includes an outer ring and an inner hub defining an airflow passage therebetween, the outer ring having an axis defining an axial direction; a plurality of struts arranged in a circumferential array and extending radially from the inner hub to the outer ring to mount the inner hub to the outer ring; wherein the outer ring is defined by a double skin including an axially-extending annular outer skin of sheet metal concentrically surrounding and radially-spaced from an annular inner skin of sheet metal, the outer and inner skins generally parallel to one another, an annular front end ring and an annular rear end ring welded or brazed to the outer and inner skins adjacent respective front and rear edges of the skins to define an annular cavity between them, and the outer ring further comprising a plurality of circumferentially spaced axially-extending ribs interconnecting the outer and inner skins to reinforce the double skins.
Abstract translation: 一种用于飞行器发动机的壳体包括外圈和限定其间的气流通道的内毂，所述外圈具有限定轴向的轴线; 多个支柱，其布置成周向阵列并且从所述内毂径向延伸到所述外环以将所述内毂安装到所述外环; 其中所述外环由双层皮肤限定，所述双层皮肤包括与所述金属板的环形内表面同心地围绕并径向间隔开的轴向延伸的环形外皮，所述外表皮和内表皮大体上彼此平行， 端环和环形后端环，其与外表面和内表面相邻地焊接或钎焊，所述外表面和内表面邻近表皮的前后边缘以在其间限定环形空腔，并且所述外环还包括多个周向间隔开的轴向延伸的肋， 外皮和内皮加固双面皮。
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公开(公告)号：US08829702B1
公开(公告)日：2014-09-09
申请号：US13792739
申请日：2013-03-11
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere , Andreas Eleftheriou , Richard Kostka
IPC: F01D15/00
CPC classification number: F02C7/275 , F02C7/36 , F05D2220/766 , H02K7/1823 , H02K15/14 , H02K23/52 , Y10T29/49009
Abstract: A gas turbine engine including high and low pressure shafts, an electromechanical device having a rotor and a stator coupled such that the rotor is rotatable with respect to the stator, the rotor having a device gear secured thereto, the device being secured to a support structure in a bearing housing forming part of a bearing assembly supporting a portion of the low pressure shaft extending in proximity of the high pressure shaft and of the shaft gear, and a coupling idle gear secured for rotation about a stationary gear support mounted in the bearing housing, the idle gear being in toothed engagement with the shaft gear and with the device gear. An electromechanical device assembly for a gas turbine engine and a method of operating an electromechanical device are also provided.
Abstract translation: 一种包括高压和低压轴的燃气涡轮发动机，具有转子和定子的机电装置，所述定子联接成使得所述转子相对于所述定子可旋转，所述转子具有固定到其上的装置齿轮，所述装置固定到支撑结构 在形成轴承组件的一部分的轴承壳体中，所述轴承组件支撑在所述高压轴和所述轴齿轮附近延伸的所述低压轴的一部分，以及联接空转齿轮，所述联接空转齿轮被固定以围绕安装在所述轴承壳体 ，空转齿轮与轴齿轮和装置齿轮啮合。 还提供了一种用于燃气涡轮发动机的机电装置组件和操作机电装置的方法。
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公开(公告)号：US20240418128A1
公开(公告)日：2024-12-19
申请号：US18211071
申请日：2023-06-16
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere
Abstract: An engine system is provided that includes an engine core assembly and a fuel system. The engine core assembly includes a core flowpath, a core compressor section, a core combustor section and a core turbine section. The core flowpath extends through the core compressor section, the core combustor section and the core turbine section from an inlet into the core flowpath to an exhaust from the core flowpath. The core compressor section includes a core compressor rotor. The combustor section includes a combustor. The fuel system includes a fuel flowpath, a fuel turbine section and a fuel injector. The fuel flowpath extends through the fuel turbine section to the fuel injector. The fuel turbine section includes a fuel turbine rotor coupled to and rotatable with the core compressor rotor. The fuel injector is configured to direct fuel received from the fuel flowpath into the combustor.
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公开(公告)号：US20240209794A1
公开(公告)日：2024-06-27
申请号：US18088202
申请日：2022-12-23
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere
CPC classification number: F02C7/36 , B64D27/10 , B64D27/24 , F02C6/20 , F02C7/32 , F05D2220/323 , F05D2220/70 , F05D2240/62 , F05D2260/40
Abstract: An engine system is provided that includes an engine rotating structure, an electric machine rotating structure and a flex coupler. The flex coupler rotatably connects the electric machine rotating structure to the engine rotating structure. The flex coupler includes a first mount, a second mount and a flex plate. The first mount includes a plurality of first mount fingers arranged circumferentially about an axis. The second mount includes a plurality of second mount fingers arranged circumferentially about the axis. The flex plate connects the first mount to the second mount. The flex plate includes a plurality of first flex plate fingers and a plurality of second flex plate fingers. Each of the first flex plate fingers is attached to a respective one of the first mount fingers. Each of the second flex plate fingers is attached to a respective one of the second mount fingers.
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公开(公告)号：US11746670B2
公开(公告)日：2023-09-05
申请号：US17562306
申请日：2021-12-27
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere , Timothy Redford
CPC classification number: F01D11/22 , F01D11/001 , F05D2220/32 , F05D2240/11
Abstract: An impeller shroud assembly for a gas turbine engine includes an annular impeller shroud disposed about an axial centerline. The impeller shroud includes a shroud inducer portion and a shroud exducer portion disposed radially outward of the shroud inducer portion and extending to an outer radial end of the impeller shroud. The shroud inducer portion and the shroud exducer portion defining an impeller-facing surface of the impeller shroud. The impeller shroud has a pivot point defined between the shroud inducer portion and the shroud exducer portion. The impeller shroud assembly further includes a clearance control device connected to the shroud exducer portion of the impeller shroud proximate the outer radial end. The clearance control device is configured to pivot the shroud exducer portion of the impeller shroud about the pivot point between a first axial position and a second axial position.
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