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    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL
    1.
    发明公开
    APPARATUS AND METHODS FOR AIRCRAFT PROPELLER CONTROL 审中-公开

    公开(公告)号：EP3974313A1

    公开(公告)日：2022-03-30

    申请号：EP21203536.4

    申请日：2017-08-17

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： YAKOBOV, Ella ,  JARVO, James Robert

    IPC分类号： B64C11/30 ,  B64C11/50

    摘要： An aircraft propeller control system for an aircraft propeller (30) with adjustable blade angle has a blade angle feedback ring (104) and a sensor (112), one of which is mounted for rotation with the propeller. The blade angle feedback ring (104) moves longitudinally along with adjustment of the blade angle and has position markers (102) circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor (112) is positioned adjacent the feedback ring (104) for producing signals indicative of passage of the position markers (102). Intervals between signals are indicative of circumferential distances between position markers (102). A controller (115) measures longitudinal position of the feedback ring (104) 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
    3.
    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：EP4353585A1

    公开(公告)日：2024-04-17

    申请号：EP23203059.3

    申请日：2023-10-11

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： KRZYWON, Jagoda ,  LACHANCE, Benoit ,  JARVO, James Robert

    IPC分类号： B64C11/40

    CPC分类号： B64C11/40 ,  B64C11/385

    摘要： A propeller blade angle control circuit (20) for a turboprop engine includes a propeller control unit (21) controlling a supply of oil to modify an angle of propeller blades (17), a pump (22) located upstream of the propeller control unit (21) and providing the supply of oil from an engine oil return system (13) to the propeller control unit (21), and a flow regulator (30) between the pump (22) and the propeller control unit (21), the flow regulator (30) modulating a supply of oil to the propeller control unit (21). A bypass (40), downstream of the pump (22) in the propeller blade angle control circuit (20), has an inlet fluidly coupled to the pump (22). The bypass (40) is operable between a closed position and an open position in which a portion of the oil supplied to the propeller control unit (21) is diverted away from the propeller blade angle control circuit (20). The open position is engaged when an oil pressure reaches a predetermined threshold.

    SYSTEM AND METHOD FOR ELECTRONIC PROPELLER BLADE ANGLE POSITION FEEDBACK
    4.
    发明公开
    SYSTEM AND METHOD FOR ELECTRONIC PROPELLER BLADE ANGLE POSITION FEEDBACK 有权
    系统公司ZER ELEKTRONISCHENPROPELLERBLATTWINKELPOSITIONSRÜCKKOPPLUNG

    公开(公告)号：EP3124377A1

    公开(公告)日：2017-02-01

    申请号：EP16189338.3

    申请日：2014-11-21

    申请人： Pratt & Whitney Canada Corp.

    发明人： DUKE, Brant ,  JARVO, James Robert ,  MARK, Michael ,  GUERRA, Mario

    IPC分类号： B64C11/30 ,  G01P3/487 ,  G01P3/488 ,  B64C11/06 ,  G01D5/245 ,  G01D5/14

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

    摘要： 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.

    摘要翻译： 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，传感器固定地邻近环形构件安装并且被配置为当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，环形构件 构件和传感器构造成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;以及检测单元，连接到传感器，用于从其接收传感器信号， 传感器信号的基础是在连续奇点的通过之间经过的时间间隔，以及从时间间隔叶片角度位置的计算。

    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE
    6.
    发明公开
    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP4325037A2

    公开(公告)日：2024-02-21

    申请号：EP23214441.0

    申请日：2020-10-12

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： JARVO, James Robert ,  SAINTIGNAN, Cedric ,  MOKHTAR, Hytham

    IPC分类号： F02C7/232

    摘要： Fuel systems of gas turbine engines (14) of aircraft, and associated methods (500, 700) can permit reverse purging of one or more fuel manifolds of a gas turbine engine (14) to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds (34A, 34B) fluidly connectable to a combustor (20) of the gas turbine engine (14). A valve (52) is operatively disposed between the second fuel manifold (34B) and a fuel supply line (58) for controlling fuel supply to the second fuel manifold (34B). A reservoir (64) includes a movable piston (66) disposed therein and dividing the reservoir (64) into a first chamber (64A) and a second chamber (64B). The first chamber (64A) is fluidly connectable to the fuel supply line (58) or to a fuel purge line (68) via the valve (52). The second chamber (64B) is in fluid communication with the second fuel manifold (34B) to receive residual fuel from the second fuel manifold (34B).

    APPARATUS AND METHOD FOR AIRCRAFT PROPELLER CONTROL
    7.
    发明公开
    APPARATUS AND METHOD FOR AIRCRAFT PROPELLER CONTROL 审中-公开
    用于飞机螺旋桨控制的装置和方法

    公开(公告)号：EP3284666A1

    公开(公告)日：2018-02-21

    申请号：EP17186725.2

    申请日：2017-08-17

    申请人： Pratt & Whitney Canada Corp.

    发明人： YAKOBOV, Ella ,  JARVO, James Robert

    IPC分类号： B64C11/30

    CPC分类号： B64D45/0005 ,  B64C11/30 ,  B64C11/301 ,  B64D35/02

    摘要： An aircraft propeller control system for an aircraft propeller (30) with adjustable blade angle has a blade angle feedback ring (104) and a sensor (112), one of which is mounted for rotation with the propeller. The blade angle feedback ring (104) moves longitudinally along with adjustment of the blade angle and has position markers (102) circumferentially spaced apart at distances that vary along a longitudinal axis. The sensor (112) is positioned adjacent the feedback ring (104) for producing signals indicative of passage of the position markers (102). Intervals between signals are indicative of circumferential distances between position markers (102). A controller (115) measures longitudinal position of the feedback ring (104) based on the intervals and is configured to produce a warning signal if the longitudinal position is outside a first threshold range.

    摘要翻译： 用于具有可调节叶片角度的飞机螺旋桨（30）的飞机螺旋桨控制系统具有叶片角度反馈环（104）和传感器（112），其中一个安装成与螺旋桨一起旋转。 叶片角度反馈环（104）随着叶片角度的调节而纵向移动，并且具有位置标记（102），所述位置标记（102）在沿着纵向轴线变化的距离处沿周向间隔开。 传感器（112）位于反馈环（104）附近，用于产生指示位置标记（102）通过的信号。 信号之间的间隔表示位置标记（102）之间的周向距离。 控制器（115）基于间隔测量反馈环（104）的纵向位置，并且被配置为如果纵向位置在第一阈值范围之外则产生警告信号。

    OVERSPEED AND/OR OVERTORQUE PROTECTION FOR HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM
    8.
    发明公开
    OVERSPEED AND/OR OVERTORQUE PROTECTION FOR HYBRID ELECTRIC AIRCRAFT PROPULSION SYSTEM 审中-实审

    公开(公告)号：EP4350135A2

    公开(公告)日：2024-04-10

    申请号：EP23201463.9

    申请日：2023-10-03

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： SYED, Yusuf ,  RICCI, Thomas Trevor ,  JARVO, James Robert

    IPC分类号： F02C6/20 ,  F02C9/48 ,  F02K5/00

    摘要： A hybrid-electric powerplant (HEP) (100) of an aircraft comprises a thermal engine (110) providing a first torque input to the HEP (100) and an electric motor (130) providing a second torque input to the HEP (100). A power management system (200; 200') connected to one or both of the thermal engine (110) and the electric motor (130) comprises an engine control unit (ECU) (210; 210') connected to the thermal engine (110). The ECU (210; 210') controls fuel supplied to the thermal engine (110). An electric propulsion control (EPC) (240) is connected to the electric motor (130) and controls power supplied to the electric motor (130). The EPC (240) includes an EPC protection module (260; 260') in communication with a power source for the electric motor (130). The EPC protection module (260; 260') disables power supplied to the electric motor (130) upon receipt of a signal indicative of one or more of an over-speed condition and an over-torque condition detected in the HEP (100).

    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE
    9.
    发明公开
    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3805540A3

    公开(公告)日：2021-07-28

    申请号：EP20201405.6

    申请日：2020-10-12

    申请人： Pratt & Whitney Canada Corp.

    发明人： JARVO, James Robert ,  SANITIGNAN, Cédric ,  MOKHTAR, Hytham

    IPC分类号： F02C7/232

    摘要： Fuel systems of gas turbine engines (14) of aircraft, and associated methods (500, 700) can permit reverse purging of one or more fuel manifolds of a gas turbine engine (14) to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds (34A, 34B) fluidly connectable to a combustor (20) of the gas turbine engine (14). A valve (52) is operatively disposed between the second fuel manifold (34B) and a fuel supply line (58) for controlling fuel supply to the second fuel manifold (34B). A reservoir (64) includes a movable piston (66) disposed therein and dividing the reservoir (64) into a first chamber (64A) and a second chamber (64B). The first chamber (64A) is fluidly connectable to the fuel supply line (58) or to a fuel purge line (68) via the valve (52). The second chamber (64B) is in fluid communication with the second fuel manifold (34B) to receive residual fuel from the second fuel manifold (34B).

    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE
    10.
    发明公开
    SYSTEMS AND METHODS FOR PURGING A FUEL MANIFOLD OF A GAS TURBINE ENGINE 审中-公开

    公开(公告)号：EP3805540A2

    公开(公告)日：2021-04-14

    申请号：EP20201405.6

    申请日：2020-10-12

    申请人： Pratt & Whitney Canada Corp.

    发明人： JARVO, James Robert ,  SANITIGNAN, Cédric ,  MOKHTAR, Hytham

    IPC分类号： F02C7/232

    摘要： Fuel systems of gas turbine engines (14) of aircraft, and associated methods (500, 700) can permit reverse purging of one or more fuel manifolds of a gas turbine engine (14) to prevent coking in some modes of operation. A fuel system includes first and second fuel manifolds (34A, 34B) fluidly connectable to a combustor (20) of the gas turbine engine (14). A valve (52) is operatively disposed between the second fuel manifold (34B) and a fuel supply line (58) for controlling fuel supply to the second fuel manifold (34B). A reservoir (64) includes a movable piston (66) disposed therein and dividing the reservoir (64) into a first chamber (64A) and a second chamber (64B). The first chamber (64A) is fluidly connectable to the fuel supply line (58) or to a fuel purge line (68) via the valve (52). The second chamber (64B) is in fluid communication with the second fuel manifold (34B) to receive residual fuel from the second fuel manifold (34B).