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11.发明申请公开(公告)号：US20210061476A1
公开(公告)日：2021-03-04
申请号：US16552136
申请日：2019-08-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel VAN DEN ENDE , Timothy REDFORD , David MENHEERE , Santo CHIAPPETTA
IPC: B64D13/08
Abstract: Systems and methods for conditioning a fluid using bleed air from a bypass duct of a turbofan engine are disclosed. In one embodiment, such system comprises a heat exchanger configured to facilitate heat transfer between a flow of bleed air from the bypass duct of the turbofan engine and the fluid, and a fluid-driven fluid propeller configured to drive the bleed air through the heat exchanger.
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公开(公告)号：US20190078460A1
公开(公告)日：2019-03-14
申请号：US15698905
申请日：2017-09-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Andrew MARSHALL , Richard A. KOSTKA
CPC classification number: F01D17/162 , F01D9/041 , F04D29/563 , F05D2240/12 , F05D2260/38 , F05D2260/53
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：US20170074285A1
公开(公告)日：2017-03-16
申请号：US15361877
申请日：2016-11-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Andrew R. MARSHALL , David MENHEERE
CPC classification number: F04D29/563 , B22F3/1055 , B22F5/009 , B23K15/0086 , B23K2101/001 , B33Y10/00 , B33Y80/00 , F01D5/143 , F01D11/12 , F01D17/162 , F04D29/023 , F04D29/164 , F04D29/542 , F05D2230/31 , F05D2300/514 , F05D2300/603 , F05D2300/608 , F05D2300/613 , Y10T29/49245
Abstract: A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections on the inner and/or outer shroud protrude into the annular gas path, each projection being at least partially circumferentially disposed between two variable vanes and located adjacent the overhang portion thereof. The projections have an angled planar surface that is substantially parallel to a plane defined by a terminal edge of the overhang portion of the variable vanes when pivoted through a vane pivot arc.
Abstract translation: 描述了一种用于燃气涡轮发动机压缩机的可变叶片组件及其制造方法。 内护罩和/或外护罩上的多个突起突出到环形气体路径中，每个突起至少部分地圆周地设置在两个可变叶片之间并且邻近其伸出部分定位。 突起具有倾斜的平坦表面，该平坦表面基本上平行于当通过叶片枢转弧线枢转时由可变叶片的悬垂部分的端部边缘限定的平面。
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公开(公告)号：US20170037776A1
公开(公告)日：2017-02-09
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
CPC classification number: F02B63/04 , B64D33/08 , B64D41/00 , F01C1/22 , F01C21/18 , F01P1/06 , F01P5/04 , F01P5/06 , F02B37/00 , F02B53/02 , F02B53/14 , F02B63/06 , F02B67/04 , F02B2053/005 , F02C5/00 , F02C7/14 , F02C7/18 , F02K5/00 , F05D2220/50 , F05D2260/213 , Y02T10/144 , Y02T10/17 , Y02T50/53 , Y02T50/672 , Y02T50/676
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.
Abstract translation: 一种用于飞行器的辅助动力单元，包括具有液体冷却剂系统的内燃机，与内燃机驱动接合并具有与内燃机的液体冷却剂系统不同的液体冷却剂系统的发电机，第一热交换器 与所述内燃机的液体冷却剂系统流体连通的第二热交换器与所述发电机的液体冷却剂系统流体连通，与所述热交换器的空气通道流体连通的排气管道， 排气管道，并且可由内燃机旋转，用于驱动通过空气通道的冷却空气流。 发动机的液体冷却剂系统可以不同于辅助动力单元的燃料和润滑系统。 还讨论了一种冷却发电机和内燃机的方法。
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公开(公告)号：US20140165533A1
公开(公告)日：2014-06-19
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
IPC: F02K3/04
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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Patent Agency Ranking
公开(公告)号：US20250084784A1
公开(公告)日：2025-03-13
申请号：US18243346
申请日：2023-09-07
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel ALECU , David MENHEERE
Abstract: Dual bypass gas turbine engines and associated methods are provides. A dual bypass turbofan gas turbine engine includes counter-rotating first and second fans through which ambient air is received and propelled in an aft direction; a first bypass duct receiving first bypass air including a first portion of the propelled air; a second bypass duct receiving second bypass air including a second portion of the propelled air; a core gas path receiving core air including a third portion of the propelled air; a compressor pressurizing the core air; an intercooler facilitating heat removal from the pressurized core air; a combustor in which the pressurized core air is mixed with fuel and ignited to generate a stream of combustion gas; a turbine extracting energy from the combustion gas; and a differential gear train apportioning an input torque received from the turbine between the first fan and the second fan.
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公开(公告)号：US20220388103A1
公开(公告)日：2022-12-08
申请号：US17337023
申请日：2021-06-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE
IPC: B23P19/04
Abstract: A tool for installing segments of a coupling having male and female couplers drivingly engaged to one another by the segments, the tool has: a coupler-engaging section engageable to the a female coupler of the couplers for radially supporting the tool relative to the female coupler about a rotation axis of the coupling; and a peripheral wall secured to the coupler-engaging section and extending circumferentially around the rotation axis, a diameter (D2) of the peripheral wall selected to allow insertion of the segments between the female coupler and the peripheral wall, the peripheral wall defining an abutting surface against which radially inner ends of the segments abut during insertion of the segments between the female coupler and the peripheral wall.
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公开(公告)号：US20210276724A1
公开(公告)日：2021-09-09
申请号：US16784591
申请日：2020-02-07
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Santo CHIAPPETTA , Timothy REDFORD , Daniel VAN DEN ENDE
Abstract: The gas turbine engine for an aircraft includes at least a low pressure spool with a low pressure turbine shaft operatively connected to at least one turbine, the low pressure turbine shaft rotatable about an engine axis, and a low pressure compressor operatively connected to a low pressure compressor shaft that is independently rotatable relative to the low pressure turbine shaft. A differential gearbox has an input operatively connected to the low pressure turbine shaft, a first output and a second output, the first output of the differential gearbox operatively connected to the low pressure compressor shaft and the second output of the differential gearbox operatively connected to an output shaft of the gas turbine engine. The differential gearbox permits the output shaft, the low pressure compressor shaft and the low pressure turbine shaft to rotate at different speeds.
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公开(公告)号：US20210003206A1
公开(公告)日：2021-01-07
申请号：US16460067
申请日：2019-07-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Richard KOSTKA , David MENHEERE
IPC: F16H57/04 , F02C7/32 , F02C7/06 , F16H57/027 , B64D33/00
Abstract: The aircraft engine can have an air-oil separator having an air-oil mixture inlet, an oil outlet, an air outlet, and a pressure relief path provided fluidly in parallel with the air-oil separator, between the air-oil mixture inlet and the air outlet, the pressure relief path can have a pressure relief valve for evacuating air-oil mixture to the exhaust duct in the event of excess pressure in the auxiliary gearbox.
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公开(公告)号：US20200318541A1
公开(公告)日：2020-10-08
申请号：US16451548
申请日：2019-06-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David MENHEERE , Richard KOSTKA , Steven STRECKER
IPC: F02C7/047
Abstract: An anti-icing system for a gas turbine engine comprises a closed circuit containing a phase-change fluid, at least one heating component for boiling the phase-change fluid, the anti-icing system configured so that the phase-change fluid partially vaporizes to a vapour state when boiled by the at least one heating component. The closed circuit has an anti-icing cavity adapted to be in heat exchange with an anti-icing surface of the gas turbine engine for the phase-change fluid to release heat to the anti-icing surface and condense. A feed conduit(s) has an outlet end in fluid communication with the anti-icing cavity to feed the phase-change fluid in vapour state from heating by the at least one heating component to the anti-icing cavity, and at least one return conduit having an outlet end in fluid communication with the anti-icing cavity to direct condensed phase-change fluid from the anti-icing cavity to the at least one heating component. A method for heating an anti-icing surface of an aircraft is also provided.
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