公开(公告)号：US11913342B1

公开(公告)日：2024-02-27

申请号：US18302441

申请日：2023-04-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel Coutu ,  Pierre-Charles Payer

IPC: F01D17/14 ,  F01D17/16 ,  F04D27/02 ,  F02C9/20 ,  F02C7/042 ,  F04D27/00

CPC classification number: F01D17/14 ,  F01D17/16 ,  F02C7/042 ,  F02C9/20 ,  F04D27/002 ,  F04D27/0246 ,  F05D2270/309

Abstract: A method of operating a variable guide vane assembly of an aircraft engine, the variable guide vane assembly including guide vanes rotatable about respective spanwise axes and circumferentially distributed about a central axis, the method comprising: obtaining a target exit flow angle defined between a direction of a flow exiting the guide vanes and the central axis; predicting an exit flow angle as a function of at least a geometric angle, the exit flow angle defined between the direction of the flow exiting the guide vanes and the central axis, the geometric angle defined between the guide vanes and the central axis; and when a difference between the exit flow angle and the target exit flow angle is above a threshold, modulating the guide vanes to modify the geometric angle until the difference between the exit flow angle and the target exit flow angle is at or below the threshold.

公开(公告)号：US11814969B2

公开(公告)日：2023-11-14

申请号：US17381446

申请日：2021-07-21

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Daniel Coutu

IPC: F02C9/18 ,  F01D17/14 ,  F01D17/16 ,  F02C6/02 ,  F02C9/22

CPC classification number: F01D17/145 ,  F01D17/162 ,  F02C6/02 ,  F02C9/18 ,  F02C9/22 ,  F05D2220/323 ,  F05D2260/606 ,  F05D2270/053 ,  F05D2270/335

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.

公开(公告)号：US11674456B1

公开(公告)日：2023-06-13

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

IPC: F02C9/42 ,  F02C7/36

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.

公开(公告)号：US11668253B2

公开(公告)日：2023-06-06

申请号：US17072477

申请日：2020-10-16

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Charles Cormier ,  Daniel Coutu

IPC: F02C9/22 ,  F01D7/00 ,  F02C9/58 ,  F02K1/66

CPC classification number: F02C9/22 ,  F01D7/00 ,  F02C9/58 ,  F02K1/66 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2270/051 ,  F05D2270/304

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.

公开(公告)号：US10801441B2

公开(公告)日：2020-10-13

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

IPC: F02K1/38 ,  F02K1/48

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.