公开(公告)号：US11427304B2

公开(公告)日：2022-08-30

申请号：US16160439

申请日：2018-10-15

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain Lamarre ,  Simon Lopez

IPC: B64C11/00 ,  B64C11/30

Abstract: Methods and systems for slowing down an aircraft having a propeller. The method comprises operating the propeller at a reference speed with the propeller blades in a first position, applying a load to the propeller to slow down a rotational speed of the propeller when the propeller is in a windmilling state or just before the propeller enters the windmilling state, adjusting the propeller blades to a second position in response to the load being applied, to increase the rotational speed of the propeller back towards the reference speed, and operating the propeller at the reference speed with the propeller blades in the second position.

公开(公告)号：US20220316407A1

公开(公告)日：2022-10-06

申请号：US17220008

申请日：2021-04-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Simon Lopez ,  Jeremie Hebert

IPC: F02C9/16 ,  F02C6/20 ,  B64C11/30

Abstract: There are described methods and systems for operating an aircraft turboprop engine. The method comprises controlling a propeller of the turboprop engine based on a selected one of a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running; detecting an inflight restart of the turboprop engine; and controlling the propeller during the inflight restart in accordance with at least one of a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle during the inflight restart.

公开(公告)号：US10823113B2

公开(公告)日：2020-11-03

申请号：US15681531

申请日：2017-08-21

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sylvain Lamarre ,  Simon Lopez ,  Nicolas Des Roches-Dionne ,  Michael Conciatori

IPC: F02K1/76 ,  F02K1/17 ,  F02C9/44 ,  F02C9/58 ,  F02K1/66 ,  B64C11/30

Abstract: Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.

公开(公告)号：US11719167B2

公开(公告)日：2023-08-08

申请号：US17220008

申请日：2021-04-01

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Simon Lopez ,  Jeremie Hebert

IPC: F02C9/16 ,  B64C11/30 ,  F02C6/20

CPC classification number: F02C9/16 ,  B64C11/30 ,  F02C6/206 ,  F05D2270/021

Abstract: There are described methods and systems for operating an aircraft turboprop engine. The method comprises controlling a propeller of the turboprop engine based on a selected one of a reference propeller rotational speed and a minimum propeller blade angle while the turboprop engine is running; detecting an inflight restart of the turboprop engine; and controlling the propeller during the inflight restart in accordance with at least one of a modified reference propeller rotational speed and a modified minimum propeller blade angle to maintain an actual propeller blade angle above an aerodynamic disking angle during the inflight restart.

公开(公告)号：US11300054B2

公开(公告)日：2022-04-12

申请号：US16184297

申请日：2018-11-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Nicolas Des Roches-Dionne ,  Sylvain Lamarre ,  Simon Lopez

IPC: F02C7/26 ,  F02C7/262 ,  F02C3/06 ,  F02C9/26

Abstract: Systems and methods for controlling fuel flow to an engine during start are provided. Fuel is caused to be injected into a combustor of the engine according to a first fuel schedule defining a minimum fuel flow limit required to achieve light-off of the engine, the minimum fuel flow limit set at an initial value. Following light-off of the engine, at least one operating parameter of the engine is monitored. Based on the at least one operating parameter, occurrence of flameout in the engine is detected. In response to detecting occurrence of flameout in the engine, the minimum fuel flow limit is increased from the initial value to a first value to obtain an adjusted fuel schedule, and fuel is caused to be injected into the combustor according to the adjusted fuel schedule.