公开(公告)号：US20240151183A1

公开(公告)日：2024-05-09

申请号：US17983595

申请日：2022-11-09

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： James Robert JARVO ,  Cédric SAINTIGNAN ,  Hytham MOKHTAR

IPC: F02C7/232 ,  F02C7/22

CPC classification number: F02C7/232 ,  F02C7/222 ,  F05D2220/323 ,  F05D2240/35

Abstract: Fuel systems of gas turbine engines of aircraft, and associated methods are provided. The fuel systems and methods can permit reverse purging of one or more fuel manifolds of a gas turbine engine to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds fluidly connectable to a combustor of the gas turbine engine. A valve is operatively disposed between the second fuel manifold and a fuel supply line for controlling fuel supply to the second fuel manifold. A reservoir includes a movable piston disposed therein and dividing the reservoir into a first chamber and a second chamber. The first chamber is fluidly connectable to the fuel supply line or to a fuel purge line via the valve. The second chamber is in fluid communication with the second fuel manifold to receive residual fuel from the second fuel manifold.

公开(公告)号：US20180050789A1

公开(公告)日：2018-02-22

申请号：US15239779

申请日：2016-08-17

Applicant: Pratt & Whitney Canada Corp.

Inventor： Joseph Ernesto MARONE ,  James Robert JARVO ,  Ella YAKOBOV ,  Mark IACOBACCI

IPC: B64C11/30

CPC classification number: B64C11/301 ,  B63H2003/006 ,  B64C11/30 ,  G01D5/145 ,  G01D5/247

Abstract: A system and method for blade angle position feedback. The system comprises an feedback device and a sensor mounted adjacent the feedback device and configured for detecting a passage of position markers on the feedback device during propeller rotation. The position markers are spaced apart from one another around the circumference of the feedback device and are oriented at an angle to one another and to a longitudinal axis. The feedback device and sensor are configured for relative axial displacement. A detection unit is connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive position markers, and computing from the time interval blade angle position.

公开(公告)号：US20150139798A1

公开(公告)日：2015-05-21

申请号：US14546252

申请日：2014-11-18

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Brant DUKE ,  James Robert JARVO ,  Michael MARK ,  Mario GUERRA

IPC: B64C11/30 ,  F01D7/00 ,  B64D45/00

CPC classification number: B64C11/301 ,  B64C11/06 ,  B64D45/00 ,  F01D7/00 ,  G01D5/145 ,  G01D5/2451 ,  G01P3/487 ,  G01P3/488

Abstract: A system and method for blade angle position feedback. The system comprises an annular member operatively connected to rotate with a propeller, a sensor fixedly mounted adjacent the annular member and configured for detecting a passage of each singularity as the annular member is rotated and axially displaced and for generating a sensor signal accordingly, the annular member and sensor configured for relative axial displacement between a first relative axial position and a second relative axial position respectively corresponding to the first and the second mode of operation, and a detection unit connected to the sensor for receiving the sensor signal therefrom, determining on the basis of the sensor signal a time interval elapsed between the passage of successive singularities, and computing from the time interval blade angle position.

Abstract translation: 一种用于叶片角位置反馈的系统和方法。 该系统包括可操作地连接以与螺旋桨一起旋转的环形构件，固定地邻近环形构件安装的传感器，并且构造成用于在环形构件旋转并轴向移位时检测每个奇异点的通道，并相应地产生传感器信号， 构件和传感器被配置为分别对应于第一和第二操作模式的第一相对轴向位置和第二相对轴向位置之间的相对轴向位移，以及连接到传感器的检测单元，用于从其接收传感器信号， 传感器信号的基础是在连续奇异点通过之间经过的时间间隔以及从时间间隔叶片角度位置计算。

公开(公告)号：US20240270398A1

公开(公告)日：2024-08-15

申请号：US18441405

申请日：2024-02-14

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Mert CEVIK ,  James Robert JARVO ,  Keith MORGAN ,  Elizabeth GIOIA

IPC: B64D31/18 ,  B64D27/33

CPC classification number: B64D31/18 ,  B64D27/33

Abstract: A method of operating a hybrid engine for an aircraft, the hybrid engine having a thermal engine and an electric motor. The method includes verifying, using an engine control unit of the hybrid engine, that a selected power level is under a predetermined threshold for operation of the hybrid engine in a sub-idle hybrid mode. The method further includes operating the hybrid engine in the sub-idle hybrid mode, using the engine control unit, by controlling the thermal engine to operate in a standby mode, and by controlling the electric motor to operate in an active mode wherein the electric motor provides a majority of a propulsive power to the aircraft, wherein in the standby mode the thermal engine operates in a sub-idle condition to provide at most minimal propulsive power to the aircraft.

公开(公告)号：US20240113513A1

公开(公告)日：2024-04-04

申请号：US17937871

申请日：2022-10-04

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Yusuf SYED ,  Thomas Trevor RICCI ,  James Robert JARVO

IPC: H02H7/08 ,  B60W10/08

CPC classification number: H02H7/0833 ,  B60W10/08

Abstract: A hybrid-electric powerplant (HEP) of an aircraft comprises a thermal engine providing a first torque input to the HEP and an electric motor providing a second torque input to the HEP. A power management system connected to one or both of the thermal engine and the electric motor comprises an engine control unit (ECU) connected to the thermal engine. The ECU controls fuel supplied to the thermal engine. An electric propulsion control (EPC) is connected to the electric motor and controls power supplied to the electric motor. The EPC includes an EPC protection module in communication with a power source for the electric motor. The EPC protection module disables power supplied to the electric motor upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP.

公开(公告)号：US20230340910A1

公开(公告)日：2023-10-26

申请号：US18216954

申请日：2023-06-30

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： James Robert JARVO ,  Cedric SAINTIGNAN ,  Joseph Daniel Maxim CIRTWILL ,  Kian MCCALDON ,  Marc-Andre TREMBLAY ,  David WADDLETON

IPC: F02C7/30 ,  F02C7/236 ,  F02C7/232 ,  F02C7/22 ,  F02C9/32 ,  F02C9/42 ,  F02C7/228 ,  F02C6/00 ,  F02C6/16

CPC classification number: F02C7/30 ,  F02C6/00 ,  F02C6/16 ,  F02C7/222 ,  F02C7/228 ,  F02C7/232 ,  F02C7/236 ,  F02C9/32 ,  F02C9/42

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 a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.

公开(公告)号：US20220177155A1

公开(公告)日：2022-06-09

申请号：US17682349

申请日：2022-02-28

Applicant: PRATT & WHITNEY CANADA CORP.

Inventor： Ella YAKOBOV ,  James Robert JARVO

IPC: B64D45/00 ,  B64C11/30 ,  B64D35/02

Abstract: An aircraft propeller control system for an aircraft propeller with adjustable blade angle has a blade angle feedback ring and a sensor, one of which is mounted for rotation with the propeller. The blade angle feedback ring moves longitudinally along with adjustment of the blade angle and has position markers circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor is positioned adjacent the feedback ring for producing signals indicative of passage of the position markers. Intervals between signals are indicative of circumferential distances between position markers. A controller measures longitudinal position of the feedback ring based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range.