中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

37 records (took 0.023 seconds)

    Turbomachine with alternatingly spaced rotor blades
    22.
    发明授权
    Turbomachine with alternatingly spaced rotor blades 有权

    公开(公告)号：US11753939B2

    公开(公告)日：2023-09-12

    申请号：US16280531

    申请日：2019-02-20

    Applicant: General Electric Company

    Inventor： Alan Roy Stuart ,  Tsuguji Nakano ,  Thomas Ory Moniz ,  Andrew Breeze-Stringfellow ,  Richard Schmidt

    IPC: F01D5/06

    CPC classification number: F01D5/06 ,  F05D2220/32

    Abstract: A gas turbine engine is provided including a turbine section including a turbine having a plurality of first speed turbine rotor blades; a compressor section including a compressor having a plurality of first speed compressor rotor blades and a plurality of second speed compressor rotor blades; a gearbox; and a first spool rotatable by the plurality of first speed turbine rotor blades, the first spool coupled to the plurality of first speed compressor rotor blades for driving the plurality of first speed compressor rotor blades in a first direction and to the plurality of second speed compressor rotor blades across the gearbox for driving the plurality of second speed compressor rotor blades in a second direction, opposite the first direction.

    Compact Compressor
    25.
    发明申请
    Compact Compressor 有权

    公开(公告)号：US20220268209A1

    公开(公告)日：2022-08-25

    申请号：US17181773

    申请日：2021-02-22

    Applicant: General Electric Company

    Inventor： Vinod Shashikant Chaudhari ,  Bhaskar Nanda Mondal ,  Tsuguji Nakano ,  David W. Crall

    IPC: F02C6/20 ,  F02C3/04 ,  F04D25/16

    Abstract: Methods, apparatus, systems and articles of manufacture for compact compressors are disclosed including a gas turbine engine defining an axial direction and a radial direction, the gas turbine engine including an axial flow compressor and a radial flow compressor, wherein the axial flow compressor is located axially forward of the radial flow compressor, a blade assembly including a splitter shroud to divide incoming air into axial air flow for the axial flow compressor and radial air flow for the radial flow compressor, the blade assembly rotating relative to the axial flow compressor and counter-rotating relative to the radial flow compressor, and wherein the blade assembly is located axially aft of the radial flow compressor.

    ROTOR BLADES WITH PASSAGEWAYS
    29.
    发明申请
    ROTOR BLADES WITH PASSAGEWAYS 有权

    公开(公告)号：US20250075623A1

    公开(公告)日：2025-03-06

    申请号：US18242079

    申请日：2023-09-05

    Applicant: General Electric Company

    Inventor： Tsuguji Nakano ,  Andrew Breeze-Stringfellow

    IPC: F01D5/16 ,  F01D5/14

    Abstract: A rotor blade comprises an elongated body that has a pressure side and a suction side. The pressure side and suction side intersect at a leading edge and a trailing edge. The elongated body extends outward from a rotor hub. A span is described by a first straight line distance extending outward from the rotor hub along the elongated body. A chord of the elongated body is defined by a second straight-line distance extending between the leading edge and the trailing edge. At least one passageway extends through the elongated body between the pressure side and the suction side allowing a corrective flow of air to move from the pressure side to the suction side. The corrective flow of air interacts with and energizes low momentum airflow occurring along the suction side.

Patent Agency Ranking