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    TWO STAGE FUEL DELIVERY SYSTEM FOR AN AIRCRAFT
    8.
    发明公开
    TWO STAGE FUEL DELIVERY SYSTEM FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP4310307A1

    公开(公告)日：2024-01-24

    申请号：EP23184295.6

    申请日：2023-07-07

    申请人： Hamilton Sundstrand Corporation

    发明人： SUSCA, Ryan Prescott ,  HAUGSJAAHABINK, Todd ,  MASTROCOLA, Naison E. ,  STOICESCU, Adrian L. ,  LEDUC, Zachary Allen Ray ,  BRIGGS, Eric ,  O'RORKE, Morgan

    IPC分类号： F02C7/232 ,  F02C7/236 ,  F02C9/26

    摘要： A two stage fuel delivery system (20) for an aircraft includes a first stage pump (28) including an inlet (36) connected to a source of fuel and an outlet (38) connected to a combustor assembly, and a second stage pump (30) including an inlet portion (40) connected to the source of fuel and an outlet portion (42) connected to the combustor assembly. A bypass valve (46) is connected between the source of fuel, the inlet (36), and the inlet portion (40). The bypass valve (46) selectively disconnects the second stage pump (30) from the source of fuel. A metering valve (50) is connected to the inlet (36) and the inlet portion (40). The metering valve (50) includes a metering valve inlet (54) and a metering valve outlet (56). A pressure regulating valve (58) is connected to the metering valve (50). A stage monitoring system (64) is configured to detect a change in operation of the second stage and control the bypass valve (46).

    DUAL PUMP FUEL SYSTEMS
    9.
    发明公开
    DUAL PUMP FUEL SYSTEMS 审中-公开

    公开(公告)号：EP4283103A1

    公开(公告)日：2023-11-29

    申请号：EP23175680.0

    申请日：2023-05-26

    申请人： Hamilton Sundstrand Corporation

    发明人： O'RORKE, Morgan ,  SUSCA, Ryan ,  SHOOK, Ryan

    IPC分类号： F02C7/236 ,  F02C9/26 ,  F04B23/04 ,  F15B11/17

    摘要： A fuel pump system includes a main fuel pump (102) between a system fuel inlet (104) and a system fuel outlet (106), a fuel flow path at least partially defined between the main fuel pump and the system fuel outlet, and a support fuel pump (110) between the system fuel inlet and the system fuel outlet. The support fuel pump is sized to provide more flow to the system fuel outlet, when in an active state, than the main fuel pump. The system includes a valve assembly (101) in fluid communication with the support fuel pump configured and adapted to connect the support fuel pump to the system fuel outlet, and a pressure regulating valve in fluid communication with the fuel flow path between the main fuel pump and the system fuel outlet. The system includes an EHSV (118) in fluid communication with the fuel flow path between the PRV (116) and the system fuel outlet.

    MINIMUM PRESSURE VALVE FOR AIRCRAFT FUEL SYSTEM
    10.
    发明公开
    MINIMUM PRESSURE VALVE FOR AIRCRAFT FUEL SYSTEM 审中-公开

    公开(公告)号：EP4273387A1

    公开(公告)日：2023-11-08

    申请号：EP23171374.4

    申请日：2023-05-03

    申请人： Hamilton Sundstrand Corporation

    发明人： VEILLEUX, Leo J.

    IPC分类号： F02C7/228 ,  F02C7/232 ,  F02C7/236 ,  F02C9/26

    摘要： A valve having a first segment (220) between a first outer wall (220A) and a first inner wall (220B) and has a first outer port (225A) near the first outer wall and a side port (225B) between the first inner and outer walls; a second segment (230) between a second outer wall (230A) and a second inner wall (230B) and has a second outer port (235A) near the second outer wall; a center segment (240) between the first and second inner walls, and a center port (242); and a piston (245) within the valve, having: a first piston head (250) in the first segment that slides to block and unblock the side port; a second piston head (260) in the second segment that slides between the second inner and outer walls, the second piston head having a surface area that is the same as the first piston head; and a shaft (270) connecting the first and second piston heads.