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1. 发明申请

US20200309038A1 AIR SYSTEM SWITCHING SYSTEM TO ALLOW AERO-ENGINES TO OPERATE IN STANDBY MODE 审中-公开
公开(公告)号：US20200309038A1
公开(公告)日：2020-10-01
申请号：US16366293
申请日：2019-03-27
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Kevin NG , Johnny VINSKI , Adam LOGAN
IPC分类号： F02C9/18 , F01D17/08 , F02C3/34 , F16K31/12 , F02C7/32
摘要： A method of operating a multi-engine aircraft having two or more gas turbine engines includes operating a first engine in a powered mode to provide motive power to the aircraft, and, in flight, operating a second engine in either a powered mode to provide motive power to the aircraft or in a standby mode to provide substantially no motive power to the aircraft. When operating the second engine in the powered mode, pressurized air is bled from a first bleed location of a compressor of the second engine. When operating the second engine in the standby mode, pressurized air is bled from a second bleed location of the compressor of the second engine and supplying the pressurized air to a bleed air system of the second engine. The second bleed location is downstream of the first bleed location within the compressor of the second engine.

2. 发明申请

US20180340439A1 AXIALLY COMPACT PRESSURIZED SEAL 审中-公开
公开(公告)号：US20180340439A1
公开(公告)日：2018-11-29
申请号：US15606695
申请日：2017-05-26
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Johnny VINSKI
IPC分类号： F01D11/04 , F16J15/00 , F16J15/447 , F01D25/16 , F01D25/18
摘要： A seal assembly for a turbine engine having a shaft with a rotary axis and a housing surrounding the shaft; the seal assembly being disposed between the shaft and the housing, the seal assembly comprising: an outer labyrinth seal having multiple outer fins in opposing sealing engagement with a concentric outer seal runner, one of: the outer labyrinth seal fins; and the outer seal runner, engaging the housing, and the shaft engaging an opposing one of: the outer seal runner; and the outer labyrinth seal fins; an inner labyrinth seal, disposed radially inwardly concentric to and axially overlapping the outer labyrinth seal and the outer seal runner, the inner labyrinth seal having multiple inner fins in opposing sealing engagement with a concentric inner seal runner, one of: the inner labyrinth seal fins; and the inner seal runner, engaging the housing, and the shaft engaging an opposing one of: the inner seal runner; and the inner labyrinth seal fins; and an intermediate plenum, defined between the outer fins, the inner fins, the housing and the shaft, the intermediate plenum in communication with a source of compressed gas having a supply pressure greater than an ambient pressure external to the housing and greater than an internal pressure within the housing.

3. 发明申请

US20200325777A1 APEX SEAL ARRANGEMENT FOR ROTARY INTERNAL COMBUSTION ENGINE 审中-公开
公开(公告)号：US20200325777A1
公开(公告)日：2020-10-15
申请号：US16382776
申请日：2019-04-12
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Johnny VINSKI , David GAGNON-MARTIN , Jean-Gabriel GAUVREAU , Roger HUPPE
IPC分类号： F01C19/10 , F01C19/02
摘要： A rotor assembly for a rotary internal combustion engine is provided. The rotor assembly includes a rotor having a radial groove defined radially in a peripheral surface of the rotor. The groove has a depth and an intermediate shoulder at an intermediate depth. The groove has a first width therealong that is narrower than an intermediate width at the shoulder. An apex seal is received in the groove and protrudes from the peripheral face of the rotor. The apex seal is configured to move radially between a first position and a second position outward of the first position. A biasing member biases the apex seal toward the second position. A platform is disposed in the groove between the apex seal and the biasing member and has a width greater than the first width.

4. 发明申请

US20200095931A1 MULTI-SOURCE AIR SYSTEM AND SWITCHING VALVE ASSEMBLY THEREFOR 审中-公开
公开(公告)号：US20200095931A1
公开(公告)日：2020-03-26
申请号：US16140721
申请日：2018-09-25
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Johnny VINSKI
IPC分类号： F02C6/08 , F02C7/32 , F02C3/04 , F04D27/02
摘要： A method of operating a gas turbine engine having a high pressure compressor and a secondary air system includes, when the gas turbine engine is operating in a first power range, providing a first bleed source for the secondary air system by bleeding air from a first bleed location, providing bleed air at a first pressure, proximate to an outlet of the high pressure compressor. When the gas turbine engine is operating in a second power range, higher than the first power range, the method includes providing a second bleed source by bleeding air from both a second bleed location and a third bleed location. The second and third bleed locations, respectively providing bleed air at second and third pressures, are both disposed upstream of the first bleed location within the gas turbine engine. The second and third pressures are different from the first pressure.

5. 发明申请

US20180274444A1 VALVE ASSEMBLY WITH OIL SHUT-OFF VALVE 审中-公开
公开(公告)号：US20180274444A1
公开(公告)日：2018-09-27
申请号：US15990743
申请日：2018-05-28
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Charles FAUBERT , Johnny VINSKI , Valeri SOUKHOSTAVETS
IPC分类号： F02C7/06 , F16K3/32 , F16K17/02 , F16K31/12 , F16K3/02
CPC分类号： F02C7/06 , F16K3/029 , F16K3/26 , F16K3/32 , F16K17/02 , F16K31/12 , F16K31/1221 , F16K31/1225 , F16K31/1226
摘要： A gas turbine engine valve assembly having an oil shut-off valve and a compensating valve fluidly connected thereto. The compensating valve, in a first position, restricts access to a pressure-reducing oil flow path leading to an oil reservoir, and in a second position, provides access to the pressure-reducing oil flow path. The pressure-reducing oil flow path is defined by fluid flow between housing apertures, a laminar hole and an orifice. The valve assembly is operable between a first configuration, wherein the oil shut-off valve is in a fluid transfer position and a piston of the compensating valve is in a closed position to direct oil toward the engine component, and a second configuration, wherein the oil shut-off valve is in the shut-off position and the piston is in a open position to direct oil toward the oil reservoir via the pressure-reducing oil flow path.

6. 发明申请

US20140290265A1 GAS TURBINE ENGINE WITH TRANSMISSION 审中-公开
标题翻译：气体涡轮发动机与传动
公开(公告)号：US20140290265A1
公开(公告)日：2014-10-02
申请号：US13754304
申请日：2013-01-30
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Richard ULLYOTT , Keith MORGAN , Jean DUBREUIL , Lazar MITROVIC , Kevin A. DOOLEY , Stephen KENNY , Ilya MEDVEDEV , Johnny VINSKI
IPC分类号： F02C7/36
CPC分类号： F02C7/36 , F02C3/113 , F05D2220/324 , F05D2220/327
摘要： A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.
摘要翻译：具有差速器的多线轴燃气涡轮发动机具有可选择性地旋转的构件，其转速确定差速器的驱动和驱动构件的转速之间的可变比。被驱动构件接合到第一卷轴，并且与其它卷轴（例如，连接到压缩机转子）无关的可旋转轴接合到驱动构件。第一和第二动力传递装置分别接合到第一卷轴和可选择性旋转的构件。电路将功率传输装置互连并允许它们之间的电力传输，并且控制单元控制在功率传输装置之间传输的功率。因此能够在第一卷轴和可选择性地旋转的构件之间传递动力，以改变第一卷轴和可旋转轴之间的速比。

7. 发明申请

US20220213838A1 AIR SYSTEM SWITCHING SYSTEM TO ALLOW AERO-ENGINES TO OPERATE IN STANDBY MODE 有权
公开(公告)号：US20220213838A1
公开(公告)日：2022-07-07
申请号：US17649866
申请日：2022-02-03
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Kevin NG , Johnny VINSKI , Adam LOGAN
IPC分类号： F02C6/02 , B64D35/08 , F02C6/04 , F02C9/18
摘要： A multi-engine aircraft includes a first engine drivingly engaged to a common rotatable load and a second engine drivingly engaged to the common rotatable load, the second engine having a bleed air system and a control system in communication with a compressed air switching system. The control system controls operation of the second engine and/or the compressed air switching system. The compressed air switching system includes a switching valve that is displaceable between at least a first position and a second position, the first position interconnecting a lower pressure inlet and a switch outlet, and the second position interconnecting a high pressure inlet and the switch outlet. The switch outlet is in communication with the bleed air system of the second engine. The control system actuates the switching valve to switch between the first and second positions.

8. 发明申请

US20180193770A1 AIR-OIL SEPARATION APPARATUS 审中-公开
公开(公告)号：US20180193770A1
公开(公告)日：2018-07-12
申请号：US15400560
申请日：2017-01-06
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Marcin CZAJKOWSKI , Sebastien BERGERON , Filip Adam PULTER , Johnny VINSKI
IPC分类号： B01D19/00 , F01D25/18
摘要： The described air-oil separation apparatus for an oil system of a gas turbine engine includes an oil tank having an oil impingement surface disposed on a tank bottom proximate an oil tank outlet and a centrifugal air-oil separator mounted within the oil tank. The centrifugal air-oil separator has an oil outlet that feeds an impingement nozzle having an outlet oriented, in operation, to eject an oil jet from the centrifugal air-oil separator to impinge the oil impingement surface at an intersection point spaced apart from the oil tank outlet.

9. 发明申请

US20180172078A1 SPLINE ALIGNMENT 审中-公开
公开(公告)号：US20180172078A1
公开(公告)日：2018-06-21
申请号：US15380193
申请日：2016-12-15
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Johnny VINSKI , Eric DUROCHER
IPC分类号： F16D1/06 , F02C7/36 , F01D5/02
CPC分类号： F16D1/06 , F01D5/026 , F02C7/36 , F05D2250/11 , F05D2260/36 , F16D1/0894 , F16D1/112 , F16D2001/103 , Y10T29/49895 , Y10T29/49897 , Y10T403/7032
摘要： A gas turbine shaft assembly comprises first and second axially mating shafts. The first shaft has a circumferential array of splines configured to mesh with a corresponding circumferential array of splines on the second shaft. The first shaft defines at least one axially extending slot aligned with one of the splines on the first shaft. The second shaft has at least one radial projection aligned with one of the splines on the second shaft. The engagement of the radial projection with the slot provides angular correspondence between the splines of the first and the second shafts prior to axial engagement of the splines.

10. 发明申请

US20190010875A1 GAS TURGINE ENGINE WITH TRANSMISSION 审中-公开
公开(公告)号：US20190010875A1
公开(公告)日：2019-01-10
申请号：US16123344
申请日：2018-09-06
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Richard ULLYOTT , Keith MORGAN , Jean DUBREUIL , Lazar MILTROVIC , Kevin A. DOOLEY , Stephen KENNY , Ilya MEDVEDEV , Johnny VINSKI
IPC分类号： F02C7/36 , F02C3/113
摘要： A multi spool gas turbine engine with a differential having a selectively rotatable member which rotational speed determines a variable ratio between rotational speeds of driven and driving members of the differential. The driven member is engaged to the first spool and a rotatable shaft independent of the other spools (e.g. connected to a compressor rotor) is engaged to the driving member. First and second power transfer devices are engaged to the first spool and the selectively rotatable member, respectively. A circuit interconnects the power transfer devices and allows a power transfer therebetween, and a control unit controls the power being transferred between the power transfer devices. Power can thus be transferred between the first spool and the selectively rotatable member to change the speed ratio between the first spool and the rotatable shaft.

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