中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

16 records (took 0.023 seconds)

    Fan blade having closed metal sheath
    1.
    发明授权
    Fan blade having closed metal sheath 有权

    公开(公告)号：US11499566B2

    公开(公告)日：2022-11-15

    申请号：US17196359

    申请日：2021-03-09

    Applicant: RAYTHEON TECHNOLOGIES CORPORATION

    Inventor： Jason Husband ,  James Glaspey

    IPC: F04D29/38 ,  F01D5/14 ,  F01D5/18 ,  F04D19/00 ,  F04D29/32 ,  F04D29/64 ,  F04D29/02 ,  F01D5/12 ,  B23P15/04

    Abstract: A method for forming a blade for a gas turbine engine may include forming a suction side sheath and a pressure side sheath, a first cavity and a second cavity established on opposed sides of a rib, forming a structural core configured for positioning in an interior section of the blade between the suction side sheath and the pressure side sheath, the structural core including a first core member, a second core member and a root interconnecting the first and second core members, assembling the suction side sheath and the pressure side sheath with the structural core such that the first core member is positioned in the first cavity and such that the second core member is positioned in the second cavity, and securing the suction side sheath to the pressure side sheath to form the blade.

    HYBRID AIRFOIL FOR GAS TURBINE ENGINES
    2.
    发明申请
    HYBRID AIRFOIL FOR GAS TURBINE ENGINES 有权

    公开(公告)号：US20210231020A1

    公开(公告)日：2021-07-29

    申请号：US17030860

    申请日：2020-09-24

    Applicant: Raytheon Technologies Corporation

    Inventor： Jason Husband ,  James Glaspey

    IPC: F01D5/30 ,  F01D5/14 ,  F01D5/28

    Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a root section. The airfoil section includes a sheath that receives a core. The core includes first and second ligaments received in respective internal channels defined by the sheath, and each one of the first and second ligaments includes at least one interface portion in the root section dimensioned to receive a retention pin.

    Airfoil attachment for gas turbine engines
    3.
    发明授权
    Airfoil attachment for gas turbine engines 有权

    公开(公告)号：US11073030B1

    公开(公告)日：2021-07-27

    申请号：US16879862

    申请日：2020-05-21

    Applicant: Raytheon Technologies Corporation

    Inventor： Jason Husband ,  David A. Welch

    IPC: F01D5/30 ,  F01D5/32 ,  F01D5/22 ,  F01D5/28

    Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil including an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a circumferential direction. A root mount includes first and second mount members secured to circumferentially opposed sides of the root section. Arcuate circumferential faces of the first and second mount members are dimensioned to pivotably mount the root section to a hub in an installed position. A method of assembly is also disclosed.

Patent Agency Ranking