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    Turbomachine Cooling Trench
    45.
    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
    46.
    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.

    COMPONENT WITH COOLING PASSAGE FOR A TURBINE ENGINE
    49.
    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

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Zachary Daniel Webster ,  Daniel Endecott Osgood ,  Kirk Douglas Gallier

    IPC: F01D5/18 ,  F01D5/08

    CPC classification number: F01D5/187 ,  F01D5/087 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/201 ,  F05D2260/232

    Abstract: 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.

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