公开(公告)号：US20200256304A1

公开(公告)日：2020-08-13

申请号：US16274384

申请日：2019-02-13

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Michael YOUSSEF ,  Alexandre CHAREST ,  Giancarlo ZINGARO ,  Jasraj CHAHAL ,  Carmine LISIO ,  Darragh MCGRATH

IPC: F02N11/08

Abstract: Methods and systems for starting an aircraft propulsion engine are described herein. Operation of the engine is controlled by an engine controller having a first channel and a second channel. An engine start request is received on the second channel while the first channel is inactive. It is determined which one of the first channel and the second channel was used to conduct a last successful engine start. Responsive to determining that the last successful engine start was conducted on the second channel, a predetermined time period is waited to elapse and for the first channel to reinitialize before commanding, via the first channel, an engine start based on the engine start request.

公开(公告)号：US20210341530A1

公开(公告)日：2021-11-04

申请号：US16862685

申请日：2020-04-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Reza PEDRAMI ,  Carmine LISIO ,  Richard KUDRNA

IPC: G01R31/28 ,  G01R31/304

Abstract: There is provided an aircraft engine printed circuit board assembly generally having a functional circuit contributing to the operation of an aircraft engine. The functional circuit has a first substrate portion, a first electronic component supported by the first substrate portion, and a first electrical conductor supported by the first substrate portion and leading to the first electronic component. The aircraft engine printed circuit board assembly generally has a monitoring circuit having a second substrate portion, a second electronic component supported by the second substrate portion, a second electrical conductor supported by the second substrate portion and leading to the second electronic component, the second electrical conductor having a shorter life expectancy than the first electrical conductor, and a detector monitoring an indicator of operativeness of the second electrical conductor, in which the first electrical conductor and the second electrical conductor are both exposed to the same environment.

公开(公告)号：US20200232395A1

公开(公告)日：2020-07-23

申请号：US16250256

申请日：2019-01-17

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jasraj CHAHAL ,  Carmine LISIO ,  Darragh MCGRATH ,  Giancarlo ZINGARO

IPC: F02C9/58 ,  B64D31/06 ,  B64D27/10

Abstract: Methods and systems for operating a gas turbine engine coupled to an aircraft propeller are described herein. A request for reverse of the propeller thrust is received from a power lever of the aircraft. A blade angle of the propeller is determined. Reverse thrust of the propeller is inhibited when the blade angle exceeds a threshold. Reverse thrust of the propeller based on the request is enabled when the blade angle is below the threshold.

公开(公告)号：US20200164996A1

公开(公告)日：2020-05-28

申请号：US16775489

申请日：2020-01-29

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Carmine LISIO ,  Kenneth Matheson

IPC: B64D31/06 ,  B64C11/30 ,  B64D27/10 ,  F02C9/58

Abstract: There are described methods and systems for controlling an aircraft. The system comprises a power plant controller configured for controlling operation of an engine and a propeller coupled to the engine, a power throttle having at least one throttle lever to regulate output power of the engine and thrust produced by the propeller, and an autothrottle controller operatively connected to the power plant controller and to the power throttle and configured to modulate engine power without pilot input by causing a change to at least one setting of the power throttle.

公开(公告)号：US20180237125A1

公开(公告)日：2018-08-23

申请号：US15446262

申请日：2017-03-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Carmine LISIO ,  Kenneth MATHESON

IPC: B64C19/02 ,  B64D27/10 ,  B64C11/30 ,  B64D31/06

CPC classification number: B64D31/06 ,  B64C11/30 ,  B64C11/303 ,  B64D27/10 ,  F02C9/58 ,  F05D2220/325 ,  F05D2270/051 ,  F05D2270/122

Abstract: There are described methods and systems for providing an autothrottle mode in a propeller-driven aircraft. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands is output to cause the setting change of the control input(s).

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：US20200165983A1

公开(公告)日：2020-05-28

申请号：US16545498

申请日：2019-08-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jasraj CHAHAL ,  Brant DUKE ,  Carmine LISIO ,  Jim R. JARVO ,  Giancarlo ZINGARO

IPC: F02C9/28 ,  B64D31/00 ,  B64D27/10

Abstract: An electronic controller for an engine and a propeller, a control system and related methods are described herein. The control system comprises the controller having a first channel and a second channel independent from and redundant to the first channel. Each channel comprises a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command and at least one propeller control command. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command and at least one propeller protection command. The control system comprises sensors for measuring the parameters of the engine and/or the propeller and effectors configured to control the engine and the propeller.

公开(公告)号：US20180237123A1

公开(公告)日：2018-08-23

申请号：US15459742

申请日：2017-03-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Carmine LISIO

IPC: B64C11/50 ,  B64D31/00

CPC classification number: B64C11/50 ,  B64C11/305 ,  B64D31/00 ,  B64D31/12

Abstract: Herein provided are methods and systems for controlling operation a first propeller of an aircraft, the first propeller associated with a first engine, the aircraft further comprising a second propeller associated with a second engine. A first requested engine power for the first engine is obtained. A second requested engine power for the second engine is obtained. The first propeller is synchronized with the second propeller by setting a first propeller command for the first propeller based on the first and second requested engine power, and the first propeller command is sent for the first propeller.

公开(公告)号：US20200269989A1

公开(公告)日：2020-08-27

申请号：US16872447

申请日：2020-05-12

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Carmine LISIO ,  Michel LABRECQUE

IPC: B64D31/00 ,  F02C3/04 ,  B64D35/00 ,  B64D27/10 ,  F02C9/00 ,  B64D31/06 ,  F02C9/58

Abstract: The present disclosure provides a method and a system for controlling operation of an engine of an aircraft. The method comprises, at a controller of the engine, obtaining an actual engine output power for the engine, the actual engine output power based on a propeller rotation speed and a propeller blade pitch angle; converting the actual engine output power to a predicted thrust value; determining an actual engine power limit associated with a thrust limit of a propeller coupled to the engine from the predicted thrust value; and setting a maximum engine power limit of the engine using the actual engine power limit associated with the thrust limit of the propeller.

公开(公告)号：US20200165984A1

公开(公告)日：2020-05-28

申请号：US16545472

申请日：2019-08-20

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Jasraj CHAHAL ,  Brant DUKE ,  Carmine LISIO ,  Jim R. JARVO ,  Giancarlo ZINGARO

IPC: F02C9/58 ,  B64D27/10 ,  B64C11/30

Abstract: An electronic controller for an engine and a propeller, a control system and related methods are described herein. The controller comprises a first channel and a second channel independent from and redundant to the first channel. Each channel having a control processor configured to receive first engine and propeller parameters and to output, based on the first engine and propeller parameters, at least one engine control command comprising instructions for controlling an operation of the engine and at least one propeller control command comprising instructions for controlling an operation of the propeller. Each channel also comprises a protection processor configured to receive second engine and propeller parameters and to output, based on the second engine and propeller parameters, at least one engine protection command comprising instructions for protecting the engine from hazardous conditions and at least one propeller protection command comprising instructions for protecting the propeller from hazardous conditions.