中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

13 records (took 0.013 seconds)

    UNDUCTED THRUST PRODUCING SYSTEM
    1.
    发明申请
    UNDUCTED THRUST PRODUCING SYSTEM 有权

    公开(公告)号：US20230021836A1

    公开(公告)日：2023-01-26

    申请号：US17382467

    申请日：2021-07-22

    Applicant: General Electric Company

    Inventor： David Baker Riddle ,  Keith Edward James Blodgett ,  Timothy Richard DePuy ,  William Joseph Bowden

    IPC: B64D27/12

    Abstract: An aircraft includes a fuselage, a wing connected to and extending outward from the fuselage, and an engine mounted to the wing. The engine includes turbomachine defining a centerline axis, a fan, and an exhaust section with an outlet nozzle. The turbomachine defines a centerline axis. The fan is connected to and is disposed upstream from the turbomachine. The fan is disposed to rotate about the centerline axis. During operation of the engine, an exhaust stream is expelled from the outlet nozzle of the exhaust section. The exhaust stream defines a mean direction of flow in the downstream direction from the exhaust section. The mean direction of flow defines a first angle with the centerline axis of the turbomachine that is greater than zero such that the centerline axis is oriented downwardly along the vertical direction relative to the mean direction of flow of the exhaust stream.

    System and method of operating a ducted fan propulsion system during aircraft taxi
    2.
    发明授权
    System and method of operating a ducted fan propulsion system during aircraft taxi 有权

    公开(公告)号：US10343786B2

    公开(公告)日：2019-07-09

    申请号：US15635356

    申请日：2017-06-28

    Applicant: General Electric Company

    Inventor： Brian Francis Nestico ,  Melanie Zoe Cox ,  Martin Kenneth Gabel ,  Keith Edward James Blodgett

    IPC: B64D33/04 ,  B64D27/16 ,  F02K3/06 ,  F02K1/72 ,  B64D29/06

    Abstract: A thrust reverser assembly and a method of operating an aircraft during a taxi mode of operation are provided. The thrust reverser assembly includes one or more actuator assemblies configured to modulate a position of a moveable portion over a continuous range of travel between a fully stowed position and a fully deployed position, such that an air flow through said thrust reverser bleed passage is correspondingly varied. The thrust reverser assembly also includes a throttle device that includes a first, ground idle power level position and a second, forward thrust mode position. Movement into the second position may be actuated separately and differently from movement into the first position. An actuator intermediate lock may inhibit actuation of the intermediate forward thrust mode of operation until a plurality of preconditions is met.

    GAS TURBINE ENGINE
    3.
    发明公开
    GAS TURBINE ENGINE 审中-公开

    公开(公告)号：US20240060430A1

    公开(公告)日：2024-02-22

    申请号：US17889927

    申请日：2022-08-17

    Applicant: General Electric Company

    Inventor： William Joseph Bowden ,  Keith Edward James Blodgett

    IPC: F01D25/24 ,  F01D25/28

    CPC classification number: F01D25/24 ,  F01D25/28 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2250/72 ,  F05D2250/38 ,  F05D2260/30

    Abstract: A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.

    System and method of operating a ducted fan propulsion system inflight
    9.
    发明授权
    System and method of operating a ducted fan propulsion system inflight 有权

    公开(公告)号：US10119495B1

    公开(公告)日：2018-11-06

    申请号：US15635384

    申请日：2017-06-28

    Applicant: General Electric Company

    Inventor： Brian Francis Nestico ,  Melanie Zoe Cox ,  Martin Kenneth Gabel ,  Keith Edward James Blodgett

    IPC: F02K1/72 ,  F02K1/76 ,  B64C9/32 ,  B64D27/16 ,  B64C13/16

    Abstract: Thrust reverser assemblies and a method of operating an aircraft during a landing approach mode of operation are provided. The thrust reverser assembly includes a moveable portion that is moveable over a continuous range of travel between a fully stowed position and a fully deployed position. Movement away from the fully stowed position opens a bleed passage. An actuator assembly coupled to the moveable portion is operable in an intermediate forward thrust mode to modulate a position of the moveable portion along the continuous range of travel, such that an air flow through the bleed passage is correspondingly varied. A throttle device includes a first position associated with deployment of, and a second position associated with engagement of, the intermediate forward thrust mode of operation. A drag flap assembly may extend from the bleed passage during the intermediate forward thrust mode of operation.

Patent Agency Ranking