中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

80 records (took 0.024 seconds)

    AERODYNAMIC TIP FEATURE
    33.
    发明申请
    AERODYNAMIC TIP FEATURE 有权

    公开(公告)号：US20210269144A1

    公开(公告)日：2021-09-02

    申请号：US17325592

    申请日：2021-05-20

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: B64C23/06

    Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

    Aerodynamic tip feature
    34.
    发明授权
    Aerodynamic tip feature 有权

    公开(公告)号：US11034436B2

    公开(公告)日：2021-06-15

    申请号：US16033583

    申请日：2018-07-12

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: B64C23/06

    Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

    NACELLE FOR AN AIRCRAFT AFT FAN
    35.
    发明申请
    NACELLE FOR AN AIRCRAFT AFT FAN 有权

    公开(公告)号：US20210107631A1

    公开(公告)日：2021-04-15

    申请号：US16987934

    申请日：2020-08-07

    Applicant: General Electric Company

    Inventor： Kishore Ramakrishnan ,  Trevor Howard Wood

    IPC: B64C21/06 ,  B64D27/20 ,  B64D33/02 ,  B64C7/02 ,  B64D27/24 ,  B64D29/04

    Abstract: An aircraft defines a longitudinal direction and includes a fuselage extending between a forward end and an aft end along the longitudinal direction of the aircraft. An aft engine is mounted to the aft end of the fuselage. The aft engine further includes a nacelle including a forward section. An airflow duct extends at least partially through the nacelle of the aft engine and defines an outlet on the forward section of the nacelle for providing an airflow to the forward section of the nacelle.

    Aerodynamic Tip Feature
    36.
    发明申请
    Aerodynamic Tip Feature 审中-公开

    公开(公告)号：US20200017200A1

    公开(公告)日：2020-01-16

    申请号：US16033583

    申请日：2018-07-12

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

    IPC: B64C23/06

    Abstract: An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.

    NOISE ATTENUATION STRUCTURES
    37.
    发明申请
    NOISE ATTENUATION STRUCTURES 审中-公开

    公开(公告)号：US20190211748A1

    公开(公告)日：2019-07-11

    申请号：US15833390

    申请日：2017-12-06

    Applicant: General Electric Company

    Inventor： Nikolai N. Pastouchenko ,  Lawrence Chih-hui Cheung ,  Umesh Paliath ,  Trevor Howard Wood ,  Hongbin Ju

    IPC: F02C7/045 ,  B64D33/02

    Abstract: Noise attenuation structures, such as acoustic liners for gas turbine engines, are provided. For example, an acoustic liner comprises a face sheet, a backing sheet spaced apart from the face sheet, and a plurality of cavities defined between the face and backing sheets. The cavities are defined by cavity walls. A plurality of backing sheet walls extends from the backing sheet toward the face sheet. The backing sheet walls extend adjacent the cavity walls, and the backing sheet is movable with respect to the face sheet such that the cavities have a variable depth. Other embodiments of noise attenuation structures also are provided.

    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN
    38.
    发明申请
    SYSTEMS AND METHODS FOR IMPROVED PROPELLER DESIGN 审中-公开

    公开(公告)号：US20190161167A1

    公开(公告)日：2019-05-30

    申请号：US15860280

    申请日：2018-01-02

    Applicant: General Electric Company

    Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché ,  Angela Knepper ,  Nicholas Bown ,  Rathakrishnan Bhaskaran

    IPC: B64C11/18 ,  B64D33/02 ,  B64C11/14

    Abstract: An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.

Patent Agency Ranking