公开(公告)号：US20230175437A1

公开(公告)日：2023-06-08

申请号：US17540570

申请日：2021-12-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Philippe BEAUCHESNE-MARTEL ,  Gaetan DE LUSSY ,  Jeremie HEBERT ,  Daniel COUTU

IPC: F02C6/20 ,  F02C6/02 ,  B64D31/00 ,  B64C27/12 ,  B64D27/10

CPC classification number: F02C6/20 ,  F02C6/02 ,  B64D31/00 ,  B64C27/12 ,  B64D27/10

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 first idle rotation speed below the placarded zone when clutched to a load; increasing a rotation speed of the first shaft from the first idle rotation speed to a flight rotation speed above the placarded zone; unclutching the second shaft from the load during the increasing; and increasing a rotation speed of the second shaft to a second idle rotation speed when the second shaft is unclutched from the load, the second idle rotation speed above the placarded zone and below the flight rotation speed.

公开(公告)号：US20230036374A1

公开(公告)日：2023-02-02

申请号：US17388308

申请日：2021-07-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel COUTU ,  Philippe BEAUCHESNE-MARTEL

IPC: F02C7/26 ,  B64D31/00 ,  F02C6/20 ,  F02C9/18

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.

公开(公告)号：US20220145811A1

公开(公告)日：2022-05-12

申请号：US17648857

申请日：2022-01-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel COUTU

IPC: F02C9/42 ,  F01D9/04 ,  F01D17/06 ,  F01D17/16 ,  F02C9/54

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.

公开(公告)号：US20190249620A1

公开(公告)日：2019-08-15

申请号：US16250325

申请日：2019-01-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Philippe BOYER ,  Daniel COUTU

IPC: F02K1/38 ,  F02K1/78

CPC classification number: F02K1/386 ,  F02K1/78

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.