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    ENGINE COMPONENT WITH COOLING HOLE
    43.
    发明申请
    ENGINE COMPONENT WITH COOLING HOLE 有权

    公开(公告)号：US20210040859A1

    公开(公告)日：2021-02-11

    申请号：US16532787

    申请日：2019-08-06

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Daniel Endecott Osgood ,  Kirk Douglas Gallier ,  Daniel Lee Durstock ,  Zachary Daniel Webster ,  Gregory Terrence Garay

    IPC: F01D5/18

    Abstract: An apparatus and method for an engine component for a turbine engine comprising an outer wall having an outer surface and bounding an interior, the outer wall defining a pressure side and a suction side, extending axially between a leading edge and a trailing edge to define a chord-wise direction, and extending radially between a root and a tip to define a span-wise direction, at least one cooling supply conduit provided in the interior, and at least one cooling passage fluidly coupling the at least one cooling supply conduit to the outer surface of the outer wall, the at least one cooling passage comprising an outlet opening onto the outer surface along the leading edge, an inlet fluidly coupled to the at least one cooling supply conduit, and a curved passage defining a curvilinear centerline.

    Turbomachine Cooling Trench
    48.
    发明申请
    Turbomachine Cooling Trench 审中-公开

    公开(公告)号：US20200040743A1

    公开(公告)日：2020-02-06

    申请号：US16055292

    申请日：2018-08-06

    Applicant: General Electric Company

    Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

    IPC: F01D5/18 ,  F01D5/14

    Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.

    FACILITATING CAPTURING AIRCRAFT FLIGHT SEGMENT
    49.
    发明申请
    FACILITATING CAPTURING AIRCRAFT FLIGHT SEGMENT 审中-公开

    公开(公告)号：US20190279439A1

    公开(公告)日：2019-09-12

    申请号：US16197032

    申请日：2018-11-20

    Applicant: General Electric Company

    Inventor： Troy Fields ,  Brendan Freely ,  Daniel Endecott Osgood ,  Eric Ruggiero

    IPC: G07C5/00 ,  G06Q50/30 ,  G06Q10/02 ,  G06Q30/02 ,  G06Q50/00 ,  G06F16/904 ,  G06F16/587

    Abstract: Systems, computer-implemented methods and/or computer program products that facilitate capturing aircraft flight segment are provided. In one embodiment, a computer-implemented method comprises: respectively providing, by a mobile computing device comprising a processor, data sets, wherein the data sets include operation, location, altitude, speed, orientation, vibration data and noise data of an aircraft; classifying, by the mobile computing device, the data sets into current flight segment, state of aircraft engine and type of engine; and generating, by the mobile computing device, a visualization regarding the current flight segment, the state of aircraft engine and the type of engine. In another embodiment, a computer-implemented method comprises: performing, by a system operatively coupled to a processor, an Internet search and aggregates historical flight information relevant to a user to determine at least one of: user lifetime air mileage, flight segments traveled, aircraft traveled, engine usage, statistics on cruise speeds, altitudes or frequent flyer miles; and scanning, by the system, the Internet search for live information displayed via social media or news outlets that is relevant to the user's travel history.

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