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：US20210025338A1

公开(公告)日：2021-01-28

申请号：US16551177

申请日：2019-08-26

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Nicolas DES ROCHES-DIONNE ,  Sylvain LAMARRE ,  Alexandre CHAREST

IPC: F02C9/28 ,  B64D31/06

Abstract: There is provided a method and system for operating a turboprop engine of an aircraft. When a resulting value for Ng is between at least one upper limit and at least one lower limit, the output power is governed as a function of the target power. When the resulting value for Ng is on or outside of the at least one upper limit and the at least one lower limit, the output power is governed as a function of the maximum Ng and the minimum Ng.

公开(公告)号：US20180348065A1

公开(公告)日：2018-12-06

申请号：US15609633

申请日：2017-05-31

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain LAMARRE ,  Alexandre CHAREST ,  Nicolas Des Roches-Dionne

IPC: G01K7/02 ,  G01K13/08 ,  G01K7/16 ,  G01K7/34 ,  F01D17/08 ,  H01C7/12 ,  G01K3/10

CPC classification number: F02C9/00 ,  F05D2260/80 ,  F05D2270/112 ,  F05D2270/3013

Abstract: Herein provided are methods and systems for detecting a high temperature condition of a gas turbine engine. A fuel flow to a combustor of the engine and a compressor outlet pressure of the engine are obtained. A ratio of the fuel flow to the compressor outlet pressure is determined. The ratio is compared to a threshold and a high temperature condition of the engine is detected when the ratio exceeds the threshold.

公开(公告)号：US20180038287A1

公开(公告)日：2018-02-08

申请号：US15361251

申请日：2016-11-25

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Gabriel MEUNIER ,  Alexandre CHAREST ,  Sylvain LAMARRE

IPC: F02C9/26 ,  F01D21/00

CPC classification number: F02C9/263 ,  F01D21/003 ,  F05D2220/32 ,  F05D2270/04 ,  F05D2270/304 ,  F05D2270/306 ,  F05D2270/54 ,  F05D2270/708

Abstract: Systems and methods for controlling an gas turbine engine are provided. The method comprises receiving a requested engine speed and obtaining a shaft inertia of the engine, a steady state fuel flow for the requested engine speed, and a relationship between fuel flow and acceleration power generated by the fuel flow. A required fuel flow to obtain the requested engine speed is determined as a function of the requested engine speed, the shaft inertia of the engine, the steady state fuel flow for the requested engine speed, and the relationship between fuel flow and acceleration power generated by the fuel flow. A command to a fuel flow metering valve is output in accordance with the required fuel flow.