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公开(公告)号：US11274556B2
公开(公告)日：2022-03-15
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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公开(公告)号：US11073103B2
公开(公告)日：2021-07-27
申请号：US16250325
申请日：2019-01-17
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Philippe Boyer , Daniel Coutu
Abstract: An exhaust mixer arrangement for a gas turbine engine comprises an exhaust cone, a lobed exhaust mixer surrounding at least a portion of the exhaust cone and a cover mounted to an outer surface of the exhaust cone. The cover and the outer surface of the exhaust cone define a dead-end cavity for receiving a stiffener ring. A plurality of circumferentially spaced-apart struts interconnect at least a number of lobes of the lobed exhaust mixer to the stiffener ring.
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公开(公告)号：US11905888B2
公开(公告)日：2024-02-20
申请号：US17390205
申请日：2021-07-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Coutu
CPC classification number: F02C7/32 , B64C27/12 , B64D27/10 , F01D15/10 , F02C6/02 , F05D2220/329 , F05D2220/76 , F05D2240/60 , F05D2260/4023 , F05D2260/4031
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：US11859554B2
公开(公告)日：2024-01-02
申请号：US17388308
申请日：2021-07-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Coutu , Philippe Beauchesne-Martel
CPC classification number: F02C7/26 , B64D31/00 , F02C6/20 , F02C9/18 , F05D2220/323 , F05D2220/74 , F05D2240/35 , F05D2260/85
Abstract: A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.
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公开(公告)号：US11486265B1
公开(公告)日：2022-11-01
申请号：US17383713
申请日：2021-07-23
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Coutu
Abstract: A variable guide vane assembly has: variable guide vanes having airfoils extending from inner ends to outer ends, the variable guide vanes pivotable about respective spanwise axes between one or more open positions and a closed position, in the closed position, trailing edge regions of the airfoils sealingly engage leading edge regions of adjacent ones of the airfoils to block an air flow; an outer wall extending around the central axis, the outer ends of the variable guide vanes pivotably engaged to the outer wall; and an inner wall extending around the central axis, the inner ends of the variable guide vanes pivotably engaged to the inner wall, the inner wall defining inner faces distributed about the central axis, a shape of the inner faces complementary to a shape of the inner ends of the airfoils to form a seal when the variable guide vanes are in the closed position.
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Patent Agency Ranking
公开(公告)号：US11274611B2
公开(公告)日：2022-03-15
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：US11939914B2
公开(公告)日：2024-03-26
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
CPC classification number: F02C6/02 , B64D27/10 , B64D31/00 , F02C6/20 , F02C9/42 , F05D2220/329 , F05D2260/96 , F05D2270/02
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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公开(公告)号：US11725595B2
公开(公告)日：2023-08-15
申请号：US17648857
申请日：2022-01-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Daniel Coutu
CPC classification number: F02C9/42 , F01D9/041 , F01D17/06 , F01D17/16 , F02C9/54 , F05D2220/323 , F05D2270/071 , F05D2270/304
Abstract: A method of operating an engine of a multi-engine aircraft includes sequentially operating the engine through a plurality of cycles, each cycle including a breathing-in phase followed by a breathing-out phase. The breathing-in phase includes: i) in response to a speed of a rotor of the engine being at a sub-idle threshold, opening variable guide vanes upstream a compressor and injecting fuel into the combustor to increase rotor speed to a pre-determined upper threshold, and then ii) in response to the rotor speed reaching the pre-determined upper threshold, reducing a supply rate of fuel into the combustor and substantially closing the variable guide vanes. The breathing-out phase includes maintaining the variable guide vanes closed at least until the speed drops from the pre-determined upper threshold to the pre-determined sub-idle threshold.
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公开(公告)号：US10927958B2
公开(公告)日：2021-02-23
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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10.发明公开公开(公告)号：US20240337219A1
公开(公告)日：2024-10-10
申请号：US18130514
申请日：2023-04-04
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Louis DURANLEAU-HENDRICKX , Daniel Coutu
IPC: F02C9/18
CPC classification number: F02C9/18 , F05D2260/80 , F05D2260/83 , F05D2270/301 , F05D2270/304 , F05D2270/71 , F05D2270/802
Abstract: Methods and systems for adjusting a modulation characteristic of a bleed-off valve of a gas turbine engine are described. The method comprises obtaining a first setpoint configuration associated with a first modulation characteristic of the bleed-off valve, obtaining operating conditions of the gas turbine engine, determining an adjustment factor based on the first setpoint configuration and the operating conditions of the gas turbine engine, and adjusting the bleed-off valve to a second setpoint configuration associated with a second modulation characteristic based on the first setpoint configuration and the adjustment factor, the second modulation characteristic being different from the first modulation characteristic.
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