公开(公告)号：US20180072402A1

公开(公告)日：2018-03-15

申请号：US15612522

申请日：2017-06-02

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David WADDLETON

IPC: B64C11/38 ,  F01M5/00

Abstract: A control circuit for changing the angle of propeller blades includes a propeller pitch change mechanism, and a fixed-displacement pump providing the supply of oil from an engine oil return system. A valve has an outlet port to direct oil from a cavity of the valve, and a pitch port in fluid communication with the pitch change mechanism. A spool of the valve is operable between a first position and a second position to respectively open and close the outlet port, and direct oil flow away from or to the pitch change mechanism.

公开(公告)号：US20240077032A1

公开(公告)日：2024-03-07

申请号：US18504453

申请日：2023-11-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Cédric SAINTIGNAN ,  Joseph Daniel Maxim CIRTWILL ,  Kian MCCALDON ,  David WADDLETON ,  Marc-André TREMBLAY ,  Ignazio BROCCOLINI ,  Stephen TARLING

IPC: F02C7/30 ,  F02C6/00 ,  F02C6/16 ,  F02C7/22 ,  F02C7/232 ,  F02C7/236 ,  F02C9/42

CPC classification number: F02C7/30 ,  F02C6/00 ,  F02C6/16 ,  F02C7/222 ,  F02C7/232 ,  F02C7/236 ,  F02C9/42 ,  F23D2209/30 ,  F23K2300/203

Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.

公开(公告)号：US20220178544A1

公开(公告)日：2022-06-09

申请号：US17116401

申请日：2020-12-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND ,  Harris SHAFIQUE ,  David WADDLETON

IPC: F23R3/36 ,  F02C7/22

Abstract: The method can include simultaneously conveying a controlled flow rate of jet fuel from a first reservoir area of the aircraft to a fuel nozzle across at least one auxiliary system, including the at least one auxiliary system using the controlled flow rate of jet fuel for operation and conveying a controlled flow rate of an alternative fuel from a second reservoir area of the aircraft to the fuel nozzle.

公开(公告)号：US20200318644A1

公开(公告)日：2020-10-08

申请号：US16376320

申请日：2019-04-05

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David WADDLETON ,  Benjamin RENAUD ,  Sebastien BERGERON ,  Etienne PLAMONDON ,  Jean-Gabriel GAUVREAU

IPC: F04D27/00 ,  F02C7/22

Abstract: A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.

公开(公告)号：US20200284205A1

公开(公告)日：2020-09-10

申请号：US16296988

申请日：2019-03-08

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： David WADDLETON ,  Benjamin RENAUD ,  Sebastien BERGERON ,  Etienne PLAMONDON ,  Jean-Gabriel GAUVREAU

IPC: F02C9/30 ,  F02C9/36 ,  F04D27/00 ,  F04D29/40 ,  F04D29/58

Abstract: A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.