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1357 条记录 (耗时 0.023 秒)

    AIRCRAFT ENGINE FLUID SYSTEM WITH BYPASS VALVE
    1.
    发明公开
    AIRCRAFT ENGINE FLUID SYSTEM WITH BYPASS VALVE 审中-公开

    公开(公告)号：US20240337200A1

    公开(公告)日：2024-10-10

    申请号：US18130643

    申请日：2023-04-04

    申请人： PRATT & WHITNEY CANADA CORP.

    发明人： Kashif MOHAMMED

    IPC分类号： F01D25/12 ,  F03G7/06

    CPC分类号： F01D25/12 ,  F02C7/14 ,  F03G7/0614 ,  F05D2260/20 ,  F05D2260/606 ,  F05D2300/505

    摘要： An aircraft engine, has: a fluid system including a component adapted for containing a volume of the fluid, the fluid circuit further including a bypass conduit bypassing the component, and a valve fluidly connected to the fluid circuit upstream of the component relative to a flow of the fluid towards the component, the valve having an open configuration fluidly connecting the source of the fluid to the bypass conduit through the valve and a closed configuration in which the valve connects the source of the fluid to the component, the valve movable from the open configuration to the closed configuration in response to the fluid being at a first temperature, and the valve movable from the closed configuration to the open configuration in response to the fluid exerting an opening force on the valve and the fluid being at a second temperature different than the first temperature.

    Gas turbine blade
    3.
    发明授权
    Gas turbine blade 有权

    公开(公告)号：US12091988B2

    公开(公告)日：2024-09-17

    申请号：US18026732

    申请日：2021-09-21

    申请人： MITSUBISHI HEAVY INDUSTRIES, LTD.

    发明人： Keita Takamura ,  Satoshi Hada

    IPC分类号： F01D5/18

    CPC分类号： F01D5/18 ,  F05D2220/32 ,  F05D2260/20

    摘要： This gas turbine blade comprises a platform part having a cooling passage formed inside, and a wing body part protruding from the upper surface of the platform part. A plurality of first ejection ports that eject a gas supplied from the cooling passage are formed in an inner chordal region of the upper surface, which is positioned further toward the wing-body side than a wing chord connecting the leading edge and the trailing edge of the wing body part. A plurality of second ejection ports that eject the gas supplied from the cooling passage are formed in an outer chordal region of the upper surface, which is positioned on the side opposite the inner chordal region with respect to the wing chord. The outer chordal region has an outer chordal leading edge region positioned on the leading-edge side and an outer chordal trailing edge region positioned on the trailing-edge side, more second ejection ports being formed in the outer chordal leading edge region than in the outer chordal trailing edge region.

    COMPONENT WITH COOLING PASSAGE FOR A TURBINE ENGINE
    4.
    发明公开
    COMPONENT WITH COOLING PASSAGE FOR A TURBINE ENGINE 审中-公开

    公开(公告)号：US20240301798A1

    公开(公告)日：2024-09-12

    申请号：US18668840

    申请日：2024-05-20

    申请人： GENERAL ELECTRIC COMPANY

    发明人： Zachary Daniel Webster ,  Daniel Endecott Osgood ,  Kirk Douglas Gallier

    IPC分类号： F01D5/18 ,  F01D5/08

    CPC分类号： F01D5/187 ,  F01D5/087 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/232

    摘要： An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.