公开(公告)号：US20220178306A1

公开(公告)日：2022-06-09

申请号：US17116410

申请日：2020-12-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND ,  Harris SHAFIQUE ,  David WADDLETON

IPC: F02C7/224 ,  B64D27/10 ,  B64D37/30 ,  B64D37/34

Abstract: The fuel system can have a jet fuel subsystem having a jet fuel conduit extending from a first reservoir area to a fuel nozzle across an auxiliary system operable using a flow of the jet fuel, at least one fuel delivery system operable to circulate a controlled flow rate of the jet fuel within said conduit and across the auxiliary system, a recirculation conduit branching off from the jet fuel conduit downstream of the auxiliary system, an actuator valve operable to selectively direct a flow of jet fuel to the at least one fuel nozzle or to the recirculation conduit; and an alternative fuel subsystem having an alternative fuel conduit extending from a second reservoir area to a fuel nozzle.

公开(公告)号：US20230184178A1

公开(公告)日：2023-06-15

申请号：US18107758

申请日：2023-02-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND

IPC: F02C9/26 ,  F02C7/236 ,  F02C3/06 ,  F02C7/262 ,  F02C9/28

CPC classification number: F02C9/26 ,  F02C7/236 ,  F02C3/06 ,  F02C7/262 ,  F02C9/28

Abstract: Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine.

公开(公告)号：US20240044294A1

公开(公告)日：2024-02-08

申请号：US18374072

申请日：2023-09-28

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Owen Ho-Yin WONG ,  John GALAS ,  Sean DURAND

IPC: F02C9/40 ,  F02C7/22 ,  F02C7/232

CPC classification number: F02C9/40 ,  F02C7/222 ,  F02C7/232 ,  F23D2209/30 ,  F23R3/36

Abstract: A fuel system can include a first fuel circuit, a second fuel circuit, and an inert gas purge system operatively connected to both the first fuel circuit and the second fuel circuit to purge at least a portion of either or both of the first and/or second fuel circuit. The first fuel can be a liquid fuel and the second fuel can be a gaseous fuel. The first fuel circuit can include a first fuel manifold configured to fluidly communicate a first fuel supply with at least one dual fuel nozzles downstream of the first fuel manifold.

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：US20210062729A1

公开(公告)日：2021-03-04

申请号：US16552200

申请日：2019-08-27

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND

IPC: F02C9/26 ,  F02C3/06 ,  F02C7/236

Abstract: Methods and systems of starting a gas turbine engine are provided. During startup, a fuel pressure associated with a primary fuel supply of the gas turbine engine is monitored. A low-pressure event for the primary fuel supply is detected when the fuel pressure falls below a predetermined threshold. Responsive to detecting the low pressure event, an electric backup boost pump is activated by an engine controller to provide fuel to the gas turbine engine.

公开(公告)号：US20200378742A1

公开(公告)日：2020-12-03

申请号：US16739052

申请日：2020-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND ,  Richard KUDRNA ,  Ian FARRELL

IPC: G01B7/30 ,  B64D31/00 ,  F01D5/02 ,  G01B7/00 ,  G01D5/14

Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and having an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device comprising a non-magnetically permeable body defining a root surface and a plurality of magnetically permeable position markers circumferentially disposed on the root surface, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.

公开(公告)号：US20200378259A1

公开(公告)日：2020-12-03

申请号：US16739044

申请日：2020-01-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Sean DURAND ,  Richard Kudrna ,  Ian Farrell

IPC: F01D5/02 ,  B64D31/00 ,  G01B7/30

Abstract: A blade angle feedback assembly for an aircraft-bladed rotor is provided. The rotor is rotatable about a longitudinal axis and has an adjustable blade pitch angle. The assembly comprises a feedback device coupled to rotate with the rotor with adjustment of the blade pitch angle, the feedback device having a root surface, a plurality of position makers circumferentially disposed on the root surface, the plurality of position markers circumferentially spaced from one another and non-aligned with the longitudinal axis, and at least one sensor mounted adjacent the feedback device and configured to detect a passage of the plurality of position markers as the feedback device rotates about the longitudinal axis.