公开(公告)号：US20200284206A1

公开(公告)日：2020-09-10

申请号：US16292684

申请日：2019-03-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean MCCARTHY ,  Patrick MANOUKIAN ,  Zachary MOUNIR FATY ,  Carmine LISIO ,  Philippe BEAUCHESNE-MARTEL

IPC: F02C9/42 ,  B64C27/12 ,  F02C6/02

Abstract: Systems and methods for operating an engine in a multi-engine rotorcraft are described herein. A first parameter indicative of torque of a first engine is obtained. A decrease of the first parameter is detected. In response to detecting the decrease of the first parameter, an autorotation of the rotorcraft is accommodated, A second parameter indicative of torque of a second engine of the rotorcraft is assessed while accommodating the autorotation. If the second parameter has not decreased, a shaft shear of the first engine is identified and accommodating of the autorotation is ended. If the second parameter has decreased, the accommodating is maintained.

公开(公告)号：US20180237165A1

公开(公告)日：2018-08-23

申请号：US15440494

申请日：2017-02-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jean-François BISSON ,  Patrick MANOUKIAN ,  Sarah THERIAULT

IPC: B64F5/60 ,  B64D41/00 ,  F01D17/24 ,  F01D21/00

CPC classification number: B64F5/60 ,  B64D41/00 ,  B64D2033/0213 ,  F01D17/24 ,  F01D21/003 ,  F05D2220/50 ,  F05D2260/83

Abstract: A method and system for operating an inlet door of an auxiliary power unit are provided. A control signal comprising at least one inlet door command is output. In response to the at least one inlet door command, at least one feedback signal is received and compared to the at least one inlet door command. If the at least one received feedback signal matches the at least one expected feedback signal, operation of the auxiliary power unit is allowed. Otherwise, operation of the auxiliary power unit is inhibited.

公开(公告)号：US20180237153A1

公开(公告)日：2018-08-23

申请号：US15440586

申请日：2017-02-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN ,  Sarah THERIAULT

IPC: B64D41/00 ,  F01D17/24 ,  F01D19/00 ,  F01D21/02 ,  F01D21/12

CPC classification number: B64D41/00 ,  B64D2033/0213

Abstract: A system and method for controlling an inlet door of an auxiliary power unit (APU) are provided. It is determined whether a condition to inhibit a start of the APU is present. If no condition to inhibit the start of the APU is present, a door-opening signal comprising instructions to cause the inlet door to be commanded to an open position in advance of a prospective command to start the APU is output. If the condition to inhibit the start of the APU is present, a door-closing signal comprising instructions to cause the inlet door to be commanded to a closed position is output.

公开(公告)号：US20220220902A1

公开(公告)日：2022-07-14

申请号：US17711445

申请日：2022-04-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN ,  Philippe BEAUCHESNE-MARTEL

IPC: F02C9/16 ,  F02C7/18 ,  F02C6/08

Abstract: A method of determining a state of a switching valve of a bleed air system in a gas turbine engine of an aircraft includes determining a temperature in a main gas path of the gas turbine engine at a location at or downstream of the combustor and then actuating the switching valve of the bleed air system to bleed air from a different bleed location. The temperature is determined after actuating the switching valve. In response to determining that a difference between the temperatures before and after the actuation of the switching valve meets a threshold, executing at least one of a first action and a second action with respect to the gas turbine engine and/or the switching valve.

公开(公告)号：US20200256265A1

公开(公告)日：2020-08-13

申请号：US16656764

申请日：2019-10-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN

IPC: F02D29/02

Abstract: Methods and systems for operating an aircraft having two or more engines are described. The method comprises operating the two or more engines of the aircraft in an asymmetric operating regime, wherein a first of the engines is in an active mode to provide motive power to the aircraft and a second of the engines is in a standby mode to provide substantially no motive power to the aircraft, receiving a request to exit the asymmetric operating regime, the request having at least one parameter associated therewith, selecting one of a plurality of available exit protocols as a function of the at least one parameter, and applying the exit protocol by commanding the engines accordingly.

公开(公告)号：US20180237149A1

公开(公告)日：2018-08-23

申请号：US15440514

申请日：2017-02-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN ,  Sarah THERIAULT

IPC: B64D33/02 ,  F02C7/042 ,  B64D41/00

CPC classification number: B64D33/02 ,  B64D41/00 ,  B64D45/0005 ,  B64D2033/0213 ,  B64D2041/002 ,  F02C7/042 ,  F05B2220/50 ,  F05B2260/80

Abstract: A system and method for controlling a position of an inlet door of an auxiliary power unit are provided. A first control signal comprising instructions for opening the inlet door to a selected one of at least a first position and a second position is output. A possible failure in a feedback signal associated with the selected one of the at least first position and second position is detected and a second control signal comprising instructions for opening the inlet door to the other one of the at least first position and second position is then output.

公开(公告)号：US20210108571A1

公开(公告)日：2021-04-15

申请号：US16599336

申请日：2019-10-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN ,  Philippe BEAUCHESNE-MARTEL

IPC: F02C9/00 ,  B64D27/10 ,  B64F5/60 ,  F02C6/20

Abstract: A method of monitoring bleed air provided from a first engine to a second engine of a multi-engine aircraft includes operating the first engine in a powered mode to provide motive power to the multi-engine aircraft; and when the first engine is in the powered mode: actuating an air valve to open an air flow path from a compressor section of the first engine to a plurality of parts of the second engine, after the step of actuating the air valve, determining a change in a temperature in a main gas path of the first engine at a location in the main gas path at or downstream of a combustor of the first engine, and in response to determining that the change is below a threshold, executing an action with respect to the first engine, the air valve, and/or the second engine.

公开(公告)号：US20200332725A1

公开(公告)日：2020-10-22

申请号：US16591857

申请日：2019-10-03

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael Paul SMITH ,  Hytham MOKHTAR ,  Daniel ARNONE ,  Patrick MANOUKIAN

IPC: F02C9/18 ,  F04D27/02

Abstract: A method of operating a gas turbine engine having a bleed air system with a switching valve, operable to switch between multiple air sources depending on an operating mode of the gas turbine engine (e.g. a motive powered mode or a standby mode), is described. The method includes operating the switching valve to provide pressurized air from a selected one or more of the multiple air sources to a cavity of the gas turbine engine having seals, and testing the switching valve to determine if the switching valve is functioning normally or abnormally. The switching valve is functioning normally when operable to switch between the multiple air sources and is functioning abnormally when switching between the multiple air sources is not possible. If the switching valve is determined to be functioning abnormally, the gas turbine engine is controlled to prevent a change of the operating mode.

公开(公告)号：US20180237152A1

公开(公告)日：2018-08-23

申请号：US15440507

申请日：2017-02-23

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN ,  Sarah THERIAULT

IPC: B64D41/00 ,  F01D17/24

CPC classification number: B64D41/00 ,  B64D2033/0213 ,  F01D17/24 ,  F02C7/057 ,  F05D2220/50 ,  F05D2270/304 ,  F05D2270/306

Abstract: There is provided a method and a system for controlling an inlet door of an auxiliary power unit provided on an aircraft. Input data indicative of whether the aircraft is on ground or airborne is received. If the aircraft is on ground, a first control signal comprising instructions to command the inlet door to a fully open position is output. If the aircraft is airborne, a second control signal comprising instructions to command the inlet door to a partially open position. When a current value of a rotational speed of the auxiliary power unit reaches a predetermined threshold indicative of an end of a start sequence of the auxiliary power unit, a third control signal comprising instructions to transition the inlet door from the partially open position to the fully open position is output.

公开(公告)号：US20210140374A1

公开(公告)日：2021-05-13

申请号：US16679901

申请日：2019-11-11

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Patrick MANOUKIAN

IPC: F02C9/18 ,  B64D31/00 ,  G05B11/28

Abstract: Methods and systems for operating a gas turbine engine in a multi-engine aircraft are described. The method comprises operating the gas turbine engine in a standby mode to provide substantially no motive power to the aircraft when another engine of the multi-engine aircraft is operated in an active mode to provide motive power to the aircraft, transitioning the gas turbine engine from the standby mode to the non-standby mode, and applying pulse width modulation to an air switching system of the gas turbine engine while transitioning the gas turbine engine from the standby mode to the non-standby mode.