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公开(公告)号：US12221971B1
公开(公告)日：2025-02-11
申请号：US18525046
申请日：2023-11-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Andrew Marshall
Abstract: A compressor has: a rotor and a shroud having a internal and external sides and an air outlet; an annular case mounted to the external side and enclosing a plenum, the annular case having inner and outer sides and defining an aperture; a valve mounted to the annular case at the aperture and having: a support secured to the annular case and defining a seat surrounding a bleed passage, the seat located on the outer side, the support defining a guiding aperture, and a valve member having a head and a stem slidably received within the guiding aperture, the valve member having a closed position and an open position, the head abutting the valve seat in the closed position and offset from the valve seat in the open position; and an actuator engaged to the valve member for moving the valve member between the closed position and the open position.
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公开(公告)号：US12116928B2
公开(公告)日：2024-10-15
申请号：US18185007
申请日：2023-03-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere
CPC classification number: F02C3/085 , F02C6/20 , F02C3/045 , F02C3/08 , F02C3/09 , F02C3/10 , F02C3/103 , F02C3/107 , F02C3/13 , F02C7/36
Abstract: An aircraft engine, has: a high-pressure spool having a high-pressure turbine drivingly engaged to a high-pressure compressor; and a low-pressure spool having: a first low-pressure turbine downstream of the high-pressure turbine; and a second low-pressure turbine downstream of the first low-pressure turbine, one or more of the first low-pressure turbine and the second low-pressure turbine drivingly engaged to a rotatable load, the first low-pressure turbine and the second low-pressure turbine radially offset from one another relative to a central axis of the aircraft engine.
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公开(公告)号：US12065972B2
公开(公告)日：2024-08-20
申请号：US18092637
申请日：2023-01-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Alecu , David Menheere
IPC: F02C7/28 , F01D9/06 , F01D25/12 , F01D25/18 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16
CPC classification number: F02C7/28 , F01D9/065 , F01D25/125 , F01D25/183 , F02C6/08 , F02C7/18 , F02C9/18 , F02C3/04 , F02C7/06 , F02C9/16 , F05D2220/32 , F05D2240/35 , F05D2240/55 , F05D2240/60 , F05D2260/221
Abstract: Systems and methods for delivering a buffer fluid to a shaft seal of a gas turbine engine are provided. An exemplary system includes, a buffer fluid source, one or more first conduits providing fluid communication between the buffer fluid source and the shaft seal along a first route, and one or more second conduits providing fluid communication between the buffer fluid source and the shaft seal along a second route different from the first route. A heat exchanger is also disposed along the first route to facilitate heat transfer between buffer fluid in the one or more first conduits and a cooling fluid.
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公开(公告)号：US11649734B1
公开(公告)日：2023-05-16
申请号：US17661148
申请日：2022-04-28
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere
CPC classification number: F01D17/00 , F01D17/16 , F01D17/165 , F05D2220/30
Abstract: A variable guide vane control system comprises an actuator and a rolling contact joint. The joint includes a drive ring rotatable about a drive axis and at least one roller rotatable about a roller axis parallel to the drive axis and drivingly connectable to a vane. A first flexible member and a second flexible member connect the drive ring and the roller to one another. The first flexible member and the second flexible member are respectively tensioned when the drive ring rotates about the drive axis in a first direction and in a second direction opposite the first direction.
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公开(公告)号：US11268405B2
公开(公告)日：2022-03-08
申请号：US16809069
申请日：2020-03-04
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Richard Kostka
Abstract: A method of manufacturing a bearing support structure of a gas turbine engine, includes: obtaining a bearing support and a casing assembly, the casing assembly having first and second casings extending around a central axis and connected together via struts, the bearing support securable to the first casing at attachment points; selecting a distance between the attachment points of the bearing support and the struts as a function of a required stiffness of the bearing support structure; and adjusting a position of the bearing support relative to the casing assembly until the attachment points are distanced from the struts by the selected distance and joining the bearing support to the casing assembly at the attachment points.
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Patent Agency Ranking
公开(公告)号：US10781756B2
公开(公告)日：2020-09-22
申请号：US15887181
申请日：2018-02-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Menheere , Daniel Alecu
Abstract: An active tip clearance control system of a gas turbine engine and an associated method are disclosed. The system comprises a Coanda effect fluidic device configured to control a flow of clearance control fluid to a turbine section of the gas turbine engine for active tip clearance control.
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公开(公告)号：US10240521B2
公开(公告)日：2019-03-26
申请号：US15227496
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 Ende
IPC: F02B39/04 , F02B39/10 , F02G3/00 , F02C5/00 , F02B53/14 , B64D41/00 , F02C6/12 , F02C7/32 , F02C7/36 , F02B33/40 , F02B37/10 , F02B37/24 , F02B39/12 , F02B61/06 , F02B63/04 , F02B53/00
Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.
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公开(公告)号：US20150275916A1
公开(公告)日：2015-10-01
申请号：US14228616
申请日：2014-03-28
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 the inner and/or outer shroud which protruded into the annular gas path such as to ensure that a radial clearance gap, defined between the projections and a vane airfoil overhang portion, remains substantially constant throughout a substantial portion of the vane pivot arc of the variable vane. The method includes forming one cavities within the shroud, the cavities isolated from the annular gas path and disposed radially beneath at least each of the projections, and providing one or more structural reinforcing elements within the cavities.
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。 多个突起，其突出到环形气体路径中的内部和/或外部护罩，以确保限定在突出部和叶片翼型件伸出部分之间的径向间隙保持在叶片枢轴的大部分内基本上恒定 可变叶片弧。 该方法包括在护罩内形成一个空腔，空腔与环形气体路径隔离并且设置在至少每个突起的径向下方，并在空腔内提供一个或多个结构增强元件。
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9.发明授权公开(公告)号：US09003638B2
公开(公告)日：2015-04-14
申请号：US13792804
申请日：2013-03-11
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere , Andreas Eleftheriou , Richard Kostka
IPC: H02K15/02
CPC classification number: H02K7/1823 , H02K15/02 , H02K15/16 , Y10T29/49002 , Y10T29/49009 , Y10T29/49012
Abstract: A method of assembling an electromechanical device in a gas-turbine engine, including mounting a rotor of the device on a rotor support, securing a stator of the device to a stator support, coupling the rotor support to the stator support such that said rotor is rotatable about said stator, securing the device to a bearing support, securing a bearing assembly on the low pressure shaft, coupling the device to the low pressure shaft by installing the bearing support over the bearing assembly, and drivingly engaging the rotor support to the high pressure shaft.
Abstract translation: 一种在气体涡轮发动机中组装机电装置的方法，包括将所述装置的转子安装在转子支撑件上，将所述装置的定子固定到定子支撑件，将所述转子支撑件联接到所述定子支撑件，使得所述转子是 可绕所述定子旋转，将所述装置固定到轴承支撑件上，将轴承组件固定在所述低压轴上，通过将所述轴承支撑件安装在所述轴承组件上并将所述转子支撑件与所述高压轴驱动地接合而将所述装置联接到所述低压轴 压力轴。
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公开(公告)号：US12215630B2
公开(公告)日：2025-02-04
申请号：US18088202
申请日：2022-12-23
Applicant: Pratt & Whitney Canada Corp.
Inventor： David Menheere
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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