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    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE
    2.
    发明申请
    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE 有权

    公开(公告)号：US20210108579A1

    公开(公告)日：2021-04-15

    申请号：US17061856

    申请日：2020-10-02

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： James Robert JARVO ,  Cédric SAINTIGNAN ,  Hytham MOKHTAR

    IPC: F02C9/42 ,  F02C7/22 ,  F02C7/228 ,  F02C7/232 ,  F02C9/38 ,  F02C9/46 ,  F01D21/00

    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.

    AIRCRAFT POWER OUTTAKE MANAGEMENT
    3.
    发明申请
    AIRCRAFT POWER OUTTAKE MANAGEMENT 审中-公开
    飞机动力输出管理

    公开(公告)号：US20160281529A1

    公开(公告)日：2016-09-29

    申请号：US15175467

    申请日：2016-06-07

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Bryan CHEN ,  Dariusz CHMIEL ,  Philippe BEAUCHESNE-MARTEL ,  James Robert JARVO

    IPC: F01D21/00 ,  G05B13/02 ,  F02C9/26 ,  F02C9/54 ,  F02C7/042

    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。

    METHOD AND SYSTEM FOR OPERATING AN AIRCRAFT POWERPLANT
    4.
    发明申请
    METHOD AND SYSTEM FOR OPERATING AN AIRCRAFT POWERPLANT 有权

    公开(公告)号：US20210102504A1

    公开(公告)日：2021-04-08

    申请号：US16713226

    申请日：2019-12-13

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： James Robert JARVO ,  Kenneth MATHESON ,  Mario GUERRA

    IPC: F02C9/58 ,  B64D31/04 ,  B64D31/06 ,  B64D27/10 ,  B64C11/44

    Abstract: Methods and system are described for operating an aircraft powerplant comprising an engine coupled to a variable-pitch propeller. The method comprises receiving a request to change a propeller rotational speed from a first setting to a second setting, determining a power need for the engine, when the power need corresponds to the second setting, modifying a command for at least one of fuel flow to the engine and oil flow to the propeller to govern the powerplant in accordance with the second setting for the propeller rotational speed, and when the power need does not correspond to the second setting, overriding the request to change the propeller rotational speed from the first setting to the second setting.

    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL
    5.
    发明申请
    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL 审中-公开

    公开(公告)号：US20180050816A1

    公开(公告)日：2018-02-22

    申请号：US15239784

    申请日：2016-08-17

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Ella YAKOBOV ,  James Robert JARVO

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

    CPC classification number: B64D45/0005 ,  B64C11/30 ,  B64C11/301 ,  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.

    BACK-UP PROTECTION FOR UNCONTROLLED FLUID PRESSURE INCREASE IN PROPELLER CONTROL UNITS
    7.
    发明公开
    BACK-UP PROTECTION FOR UNCONTROLLED FLUID PRESSURE INCREASE IN PROPELLER CONTROL UNITS 审中-公开

    公开(公告)号：US20240124125A1

    公开(公告)日：2024-04-18

    申请号：US18045958

    申请日：2022-10-12

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jagoda KRZYWON ,  Benoit LACHANCE ,  James Robert JARVO

    IPC: B64C11/38 ,  B64C11/40 ,  F03D7/02 ,  F15B20/00

    CPC classification number: B64C11/385 ,  B64C11/40 ,  F03D7/0224 ,  F15B20/008

    Abstract: A propeller blade angle control circuit for a turboprop engine includes a propeller control unit controlling a supply of oil to modify an angle of propeller blades, a pump located upstream of the propeller control unit and providing the supply of oil from an engine oil return system to the propeller control unit, and a flow regulator between the pump and the propeller control unit, the flow regulator modulating a supply of oil to the propeller control unit. A bypass, downstream of the pump in the propeller blade angle control circuit, has an inlet fluidly coupled to the pump. The bypass is operable between a closed position and an open position in which a portion of the oil supplied to the propeller control unit is diverted away from the propeller blade angle control circuit. The open position is engaged when an oil pressure reaches a predetermined threshold.

    AIRCRAFT POWER OUTTAKE MANAGEMENT
    10.
    发明申请
    AIRCRAFT POWER OUTTAKE MANAGEMENT 有权
    飞机动力输出管理

    公开(公告)号：US20140297155A1

    公开(公告)日：2014-10-02

    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

    IPC: B64D31/06

    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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