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公开(公告)号：US12221221B2
公开(公告)日：2025-02-11
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
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.
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2.发明授权公开(公告)号：US10435140B2
公开(公告)日：2019-10-08
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
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.
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公开(公告)号：US10072796B2
公开(公告)日：2018-09-11
申请号：US15209215
申请日：2016-07-13
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Reza Pedrami , James Robert Jarvo , Benjamin Renaud
CPC classification number: F16N29/02 , B63H3/08 , B64C11/00 , B64C11/303 , B64C11/40 , F16N2210/08 , F16N2230/00 , F16N2250/04 , F16N2250/08 , F16N2270/20 , G01F15/003
Abstract: There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.
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公开(公告)号：US12018616B2
公开(公告)日：2024-06-25
申请号：US17983595
申请日：2022-11-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： James Robert Jarvo , Cédric Saintignan , Hytham Mokhtar
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.
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公开(公告)号：US20210139158A1
公开(公告)日：2021-05-13
申请号：US16679879
申请日：2019-11-11
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Poi Loon TANG , Philippe Beauchesne-Martel , James Robert Jarvo
Abstract: Systems and method for filling a fuel manifold comprising at least a primary and a second manifold of a gas turbine engine are described. The method comprises providing fuel flow to the secondary manifold of the gas turbine engine, the secondary manifold being partly or completely empty; monitoring at least one engine operational parameter of the gas turbine engine as fuel fills the secondary manifold; and accelerating the engine when a transition threshold is reached, the transition threshold being associated with the engine operational parameter and indicative that fuel has reached the combustor.
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Patent Agency Ranking
公开(公告)号：US20190257777A1
公开(公告)日：2019-08-22
申请号：US16398492
申请日：2019-04-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas Trevor Ricci , Simon Sai-Ming Lam , James Robert Jarvo
Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.
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7.发明授权公开(公告)号：US12180895B2
公开(公告)日：2024-12-31
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 , F02C6/00 , F02C6/16 , F02C7/22 , 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.
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公开(公告)号：US10705038B2
公开(公告)日：2020-07-07
申请号：US16398492
申请日：2019-04-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Thomas Trevor Ricci , Simon Sai-Ming Lam , James Robert Jarvo
Abstract: There is described herein methods and systems for detecting of metallic chips in a fluid system of an aircraft engine. A resistance value is measured across a magnetic chip detector mounted to a fluid system of the aircraft engine. The resistance value is transmitted to an engine computer of the aircraft engine. In the engine computer, The resistance value is compared to a first threshold and a first warning indicative of a chip in the fluid is issued when the resistance value exceeds the first threshold.
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公开(公告)号：US09821901B2
公开(公告)日：2017-11-21
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
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.
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公开(公告)号：US09382010B2
公开(公告)日：2016-07-05
申请号：US13753158
申请日：2013-01-29
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Bryan Chen , Dariusz Chmiel , Philippe Beauchesne-Martel , James Robert Jarvo
CPC classification number: F01D21/003 , B64D31/06 , F02C7/042 , F02C9/26 , F02C9/28 , F02C9/54 , F05D2220/323 , F05D2260/83 , F05D2270/053 , G05B13/024
Abstract: A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine's condition.
Abstract translation: 一种用于控制向飞行器供电的燃气涡轮发动机的操作的系统和方法。 发动机根据从所供给的动力所得的功率的读数进行控制。 该读数被直接馈送到控制系统，该控制系统发出用于控制包括加速度参考信号，负载脱落，可变几何定位和燃料流量的发动机参数的命令。 控制系统可以进一步发出用于控制拉出量的命令。 控制系统还可以使用该读数来监视发动机的状况。
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