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    OVERSPEED AND/OR OVERTORQUE PROTECTION FOR HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM
    1.
    发明公开
    OVERSPEED AND/OR OVERTORQUE PROTECTION FOR HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM 审中-公开

    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.

    METHOD AND SYSTEM FOR DETECTING SHEAR OF A ROTATING SHAFT
    2.
    发明申请
    METHOD AND SYSTEM FOR DETECTING SHEAR OF A ROTATING SHAFT 审中-公开

    公开(公告)号：US20190292936A1

    公开(公告)日：2019-09-26

    申请号：US16131387

    申请日：2018-09-14

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Glenn BIRCH ,  Yusuf SYED

    IPC: F01D21/00 ,  F01D21/14 ,  G01M15/14

    Abstract: Systems and methods for detecting shear of a rotating shaft are described herein. A first measurement and a second measurement of a rotational speed of the shaft are acquired. The first measurement is taken at a first location along the shaft and the second measurement taken at a second location along the shaft. The first location is axially-spaced from the second location. The first and second location are on opposite sides of an expected breakage point of the shaft. A first rate of change of the rotational speed is determined from the first measurement. A second rate of change is determined from the second measurement. Shear of the shaft is detected when the first rate of change is positive and the second rate of change is negative.

    METHOD AND SYSTEM FOR THRUST REVERSER OPERATION
    3.
    发明申请
    METHOD AND SYSTEM FOR THRUST REVERSER OPERATION 有权

    公开(公告)号：US20220120239A1

    公开(公告)日：2022-04-21

    申请号：US17076192

    申请日：2020-10-21

    Applicant: PRATT & WHITNEY CANADA CORP

    Inventor： Hamza ASSI ,  Yusuf SYED ,  Ioan SABAU

    IPC: F02K1/72 ,  F02K1/76

    Abstract: There are described a system and method for operating a thrust reverser of an aircraft engine, the thrust reverser having a deployed state and a stowed state. The method comprises placing the thrust reverser in the stowed state when the thrust reverser is in the deployed state, a thrust lever associated with the engine is in a forward position, and the engine is rotating at a speed below an idle speed, wherein hydraulic pressure for stowing the thrust reverser is provided by a pump driven by the engine rotating at the speed below the idle speed.

    SYSTEM AND METHOD FOR OPERATING A MULTI-ENGINE AIRCRAFT IN AN AUXILIARY POWER UNIT MODE
    4.
    发明申请
    SYSTEM AND METHOD FOR OPERATING A MULTI-ENGINE AIRCRAFT IN AN AUXILIARY POWER UNIT MODE 审中-公开
    在辅助电源模式下操作多发动机飞机的系统和方法

    公开(公告)号：US20150251770A1

    公开(公告)日：2015-09-10

    申请号：US14196933

    申请日：2014-03-04

    Applicant: PRATT & WHITNEY CANADA CORP.

    Inventor： Jean-Francois BISSON ,  Carmine LISIO ,  Romain CHEVALIER ,  Dave SELLORS ,  Yusuf SYED ,  Guy RIVERIN ,  Matthew CHIASSON

    IPC: B64D41/00 ,  B64D31/06

    CPC classification number: B64D41/00 ,  B64D31/06 ,  B64D35/08 ,  B64D2041/002 ,  F02C7/32 ,  F02C9/42 ,  F05D2270/02 ,  F05D2270/023 ,  F05D2270/304 ,  Y02T50/44 ,  Y02T50/671

    Abstract: A first and second engine are connected to a drive train for driving an aircraft accessory. A gearbox is connected to a primer mover propulsor and an actuator operatively associated with a selected engine is moveable between a position in which the selected engine drivingly engages the gearbox for driving the propulsor and a position in which the selected engine disengages from the gearbox. A position signal, a status signal, and a request signal respectively indicative of a present position of the actuator, a governing state and present speed of each engine, and a request for movement of the actuator from the present position to the other position are received. If the selected engine's speed differs from a predetermined threshold, a control signal is output for causing the engine's speed to be adjusted towards the threshold. A control signal indicating that movement of the actuator is permitted is then output.

    Abstract translation: 第一和第二发动机连接到用于驱动飞机附件的传动系。 齿轮箱连接到起动机推动器，并且与所选择的发动机可操作地相关联的致动器可在选择的发动机驱动地接合齿轮箱以驱动推进器的位置和所选择的发动机与变速箱脱离的位置之间移动。 分别指示致动器的当前位置，每个发动机的控制状态和当前速度的位置信号，状态信号和请求信号以及致动器从当前位置到另一位置的移动请求 。 如果所选择的发动机的速度与预定的阈值不同，则输出控制信号以使发动机的速度朝向阈值进行调节。 然后输出指示执行器的移动被允许的控制信号。

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