中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

288 records (took 0.026 seconds)

    TURBINE ENGINE WITH COMPOSITE AIRFOILS
    231.
    发明申请
    TURBINE ENGINE WITH COMPOSITE AIRFOILS 有权

    公开(公告)号：US20240376903A1

    公开(公告)日：2024-11-14

    申请号：US18777725

    申请日：2024-07-19

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Arthur William Sibbach

    IPC: F04D29/38 ,  F02K3/06 ,  F04D29/02

    Abstract: A turbine engine includes a fan and a turbomachine defining an engine centerline. The turbomachine includes a compressor section, a combustion section, and a turbine section in serial flow order. The turbine engine also includes a set of composite airfoils circumferentially arranged about the engine centerline. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.

    TURBOMACHINE AND METHOD OF ASSEMBLY
    234.
    发明公开
    TURBOMACHINE AND METHOD OF ASSEMBLY 审中-公开

    公开(公告)号：US20240295224A1

    公开(公告)日：2024-09-05

    申请号：US18656056

    申请日：2024-05-06

    Applicant: General Electric Company

    Inventor： Jixian Yao ,  Trevor Howard Wood ,  Kishore Ramakrishnan ,  William Joseph Solomon ,  Giridhar Jothiprasad ,  Nicholas Joseph Kray

    IPC: F04D29/38 ,  F04D19/00

    CPC classification number: F04D29/384 ,  F04D19/002

    Abstract: A turbomachine includes an annular casing and a fan disposed inside the annular casing and mounted for rotation about an axial centerline. The fan includes fan blades that extend radially outwardly toward the annular casing. The fan blades include a composite blade including a composite airfoil section having an airfoil leading edge and an airfoil trailing edge, a root attached to the composite airfoil section, and a blade shank therebetween. A metallic leading edge shield covers an axially extending portion of the composite airfoil section including at least a portion of the airfoil leading edge and covers a radially and chordwise extending portion of the airfoil leading edge of the blade shank. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.

    TURBINE ENGINE WITH A BLADE HAVING WOVEN CORE AND TOUGHENED REGION
    237.
    发明公开
    TURBINE ENGINE WITH A BLADE HAVING WOVEN CORE AND TOUGHENED REGION 审中-公开

    公开(公告)号：US20240280026A1

    公开(公告)日：2024-08-22

    申请号：US18172723

    申请日：2023-02-22

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Arthur William Sibbach ,  Nicholas Joseph Kray ,  Gregory Carl Gemeinhardt

    IPC: F01D5/28 ,  F02C3/04

    CPC classification number: F01D5/28

    Abstract: A turbine engine comprising a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. The turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, extending between a root and a tip in a span-wise direction, and extending between a leading edge and a trailing edge in a chord-wise direction. The airfoil includes a woven core, a first bonding layer including a toughened region, and a laminate skin provided exterior of the first bonding layer and bonded to the woven core by the first bonding layer.

    Gas turbine engine rotor blade having a root section with composite and metallic portions
    238.
    发明授权
    Gas turbine engine rotor blade having a root section with composite and metallic portions 有权

    公开(公告)号：US11692444B2

    公开(公告)日：2023-07-04

    申请号：US17891312

    申请日：2022-08-19

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D5/02

    CPC classification number: F01D5/028

    Abstract: A rotor blade for a gas turbine engine includes an airfoil section and a root section extending along a longitudinal direction between an upstream surface and a downstream surface. The root section further extends along a radial direction between an inner surface positioned at an inner end of the root section and an outer end coupled to the airfoil section. Moreover, the root section extends along a circumferential direction between a first side surface and a second side surface. Furthermore, the root section defines a longitudinal centerline extending along the longitudinal direction and positioned equidistant from the inner surface and the outer end in the radial direction. The root section includes a first portion formed from a composite material and a second portion formed from a metallic material, with the longitudinal centerline extending through the second portion of the root section.

    Turbomachine rotor disk with internal bore cavity
    240.
    发明授权
    Turbomachine rotor disk with internal bore cavity 有权

    公开(公告)号：US11674395B2

    公开(公告)日：2023-06-13

    申请号：US17024212

    申请日：2020-09-17

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain

    IPC: F01D5/08 ,  B33Y80/00 ,  B23P6/00

    CPC classification number: F01D5/08 ,  B23P6/007 ,  B33Y80/00

    Abstract: A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complementary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.

Patent Agency Ranking