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公开(公告)号：US20200378316A1
公开(公告)日：2020-12-03
申请号：US16560365
申请日：2019-09-04
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel COUTU
Abstract: A method of operating a multi-engine aircraft includes operating a first engine of the aircraft to provide motive power; and operating a second engine of the aircraft in a standby mode to provide substantially no motive power, a rotor of the second engine having an idle rotational speed in the standby mode, and in the standby mode, sequentially executing cycles, a given cycle of the cycles including: opening a set of variable guide vanes upstream a compressor section of the second engine, spiking a rate of a fuel flow to a combustor of the second engine, the spiking and the opening timed to increase a rotational speed of the rotor of the second engine to an upper threshold above the idle rotational speed of the rotor, and in response to the rotational speed reaching the upper threshold, at least substantially closing the set of variable guide vanes.
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公开(公告)号：US20180142565A1
公开(公告)日：2018-05-24
申请号：US15357158
申请日：2016-11-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ignatius THERATIL , Daniel COUTU , Nicola HOULE
IPC: F01D11/12 , F16J15/3288 , F04D29/32 , F04D29/54 , F04D29/08 , F04D29/66 , F01D5/02 , F01D9/02 , F01D25/04
CPC classification number: F01D25/04 , F01D11/001 , F04D29/164 , F05D2240/56 , F05D2260/96 , F16J15/3288
Abstract: The application is directed to a brush seal assembly adapted to be operatively mounted between a stator and a rotor of a gas turbine engine. The brush seal assembly comprises a housing and a seal operatively coupled to the housing. The seal comprises at least two annular brushes each having a plurality of bristles extending away from the housing. The at least two annular brushes and the housing defines a cavity therebetween. The housing defines at least one circumferential surface within the cavity. The housing comprises at least one discontinuity defined in the at least one circumferential surface. The at least one discontinuity disrupts a continuity of annularity of the circumferential surface.
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公开(公告)号：US20230175444A1
公开(公告)日：2023-06-08
申请号：US17540574
申请日：2021-12-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Philippe BEAUCHESNE-MARTEL , Gaetan DE LUSSY , Jeremie HEBERT , Daniel COUTU
CPC classification number: F02C9/42 , F02C7/36 , F05D2220/329 , F05D2260/4023 , F05D2270/023 , F05D2270/304
Abstract: There is described a method of operating a multi-engine system of an helicopter. The multi-engine system has a first turboshaft engine having a first shaft, a second turboshaft engine having a second shaft, a gearbox having a clutch system, and a range of rotation speeds defined as a placarded zone. The method generally has: rotating the first and second shafts at a flight rotation speed above the placarded zone when clutched to a load; decreasing a rotation speed of the first shaft from the flight rotation speed to a first idle rotation speed above the placarded zone; unclutching the first shaft from the load during the decreasing; and subsequently to the decreasing and the unclutching, simultaneously decreasing the rotation speeds of the first shaft and of the second shaft to a second idle rotation speed below the placarded zone, the simultaneously decreasing including clutching the first shaft to the load.
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公开(公告)号：US20200025131A1
公开(公告)日：2020-01-23
申请号：US16204259
申请日：2018-11-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel SUMMERS-LEPINE , Philippe BOYER , Assaf FARAH , Daniel COUTU
Abstract: A gas turbine engine comprises a main gas path having an inner flow boundary wall and an outer flow boundary wall. A turbine exhaust case inner body defines a portion of the inner flow boundary wall of the main gas path. A lobed exhaust mixer defines a portion of the outer flow boundary wall of the main gas path. A stiffener ring is interconnected to at least a number lobes of the lobed exhaust mixer by a plurality of circumferentially spaced-apart struts extending through the main gas path. The stiffener ring is attached to the turbine exhaust case inner body by flexible features, such as circumferentially spaced-apart spring blades.
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公开(公告)号：US20230175436A1
公开(公告)日：2023-06-08
申请号：US17540576
申请日：2021-12-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Philippe BEAUCHESNE-MARTEL , Gaetan DE LUSSY , Jeremie HEBERT , Daniel COUTU
Abstract: There is described a method of operating a multi-engine system of an helicopter. The multi-engine system has a first turboshaft engine having a first shaft, a second turboshaft engine having a second shaft, a gearbox having a clutch system, and a range of rotation speeds defined as a placarded zone. The method generally has rotating the first shaft at a flight rotation speed when clutched and rotating the second shaft at a first idle rotation speed when unclutched, the first idle rotation speed above the placarded zone; decreasing a rotation speed of the first shaft from the flight rotation speed to a given rotation speed within the placarded zone; decreasing a rotation speed of the second shaft to the given rotation speed; clutching the second shaft; and decreasing the rotation speeds of the first and second shafts to a second idle rotation speed below the placarded zone.
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Patent Agency Ranking
公开(公告)号：US20230024094A1
公开(公告)日：2023-01-26
申请号：US17381446
申请日：2021-07-21
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel COUTU
Abstract: An aircraft engine, has: a low-pressure compressor and a high-pressure compressor located downstream of the low-pressure compressor; a gaspath valve upstream of the high-pressure compressor, the gaspath valve movable between an open configuration and a closed configuration; and a bypass flow path having in flow series a bypass inlet, a bypass valve, and a bypass outlet, the bypass inlet fluidly communicating with the gaspath upstream of at least one stage of the low-pressure compressor, the bypass valve having an open configuration in which the bypass valve allows a bypass flow and a closed configuration in which the bypass valve blocks the bypass flow, the bypass outlet fluidly communicating with the bypass inlet via the bypass valve and with the gaspath at a location in the gaspath fluidly downstream of the gaspath valve, downstream of the low-pressure compressor, and upstream of the high-pressure compressor.
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公开(公告)号：US20220120224A1
公开(公告)日：2022-04-21
申请号：US17072477
申请日：2020-10-16
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Charles CORMIER , Daniel COUTU
Abstract: A method and a system for providing in-flight reverse thrust for an aircraft are provided. The aircraft comprises an engine having a rotor, a compressor mechanically coupled to the rotor, and a variable geometry mechanism provided upstream of the compressor and configured to modulate an amount of compression work performed by the compressor. The method comprises operating the rotor with the variable geometry mechanism in a first position, receiving a request to increase reverse thrust for the rotor, in response to the request, adjusting the variable geometry mechanism from the first position towards a second position, the variable geometry mechanism having a greater opening angle in the second position than in the first position, and operating the rotor with the variable geometry mechanism in the second position for causing an increase in the amount of compression work performed by the compressor and an increase in reverse thrust for the rotor.
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公开(公告)号：US20230034946A1
公开(公告)日：2023-02-02
申请号：US17390205
申请日：2021-07-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel COUTU
Abstract: A multi-engine system for an aircraft, has: a first engine having a first output shaft, a first core shaft, and a first electric machine drivingly engaged by the first output shaft or the first core shaft; a second engine having a second output shaft, a second core shaft, and a second electric machine drivingly engaged to the second core shaft; a reduction gearbox drivingly engaged by the first output shaft and by the second output shaft for driving a common load; and a transmission path between the first engine and the second engine, the transmission path being independent from the reduction gearbox and being one or more of: a torque-transfer connection between the second core shaft and the first core shaft or the first output shaft via a coupling gearbox, and an electrical connection between the generator and the electric motor to transmit electrical power to the electric motor.
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公开(公告)号：US20200080645A1
公开(公告)日：2020-03-12
申请号：US16127714
申请日：2018-09-11
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel COUTU , Ignatius THERATIL , Nicola HOULE
IPC: F16J15/3288
Abstract: There is disclosed a brush seal assembly including at least one annular bristle pack. The at least one annular bristle pack extends circumferentially around a central axis of the brush seal assembly. The at least one annular bristle pack has bristles extending along longitudinal axes from roots to free tips. The bristles extend toward a cylindrical plane of a the seal land. Projections of the free tips on the cylindrical plane define a bristle tip projection surface being non-axisymmetric. A method of operating a brush seal assembly is also disclosed.
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公开(公告)号：US20200072056A1
公开(公告)日：2020-03-05
申请号：US16674264
申请日：2019-11-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Maksim PANKRATOV , Ignatius THERATIL , Tony CHANG , Nicola HOULE , Vincent SAVARIA , Daniel COUTU
IPC: F01D5/10
Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.
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