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    Additively Manufactured Rotating Shaft
    274.
    发明申请
    Additively Manufactured Rotating Shaft 审中-公开

    公开(公告)号：US20190234313A1

    公开(公告)日：2019-08-01

    申请号：US15883336

    申请日：2018-01-30

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Nitesh Jain ,  Srinivasarao Surapu

    IPC: F02C7/32 ,  F16C3/02 ,  B33Y80/00

    CPC classification number: F02C7/32 ,  B22F3/1055 ,  B22F5/10 ,  B33Y10/00 ,  B33Y80/00 ,  F16C3/023

    Abstract: A rotating shaft and a method for additively manufacturing the rotating shaft are provided. The rotating shaft includes an elongated body extending along an axial direction and including an inner surface that defines a hollow central portion. An internal support structure extends from the inner surface into the hollow central portion to stiffen the rotating shaft and provide a high stiffness-to-weight ratio. The internal support structures may include stiffening ribs, truss structures, mesh structures, solid disks, and/or regions having a decreased density relative to the elongated body. The elongated body and some or all internal features may be integrally formed as a single monolithic component.

    Method and system for separable blade platform retention clip
    276.
    发明授权
    Method and system for separable blade platform retention clip 有权

    公开(公告)号：US10145382B2

    公开(公告)日：2018-12-04

    申请号：US14985169

    申请日：2015-12-30

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Jan Christopher Schilling ,  Nitesh Jain ,  Abhijit Roy

    IPC: F01D11/00 ,  F04D29/32 ,  F04D29/02 ,  F01D5/14 ,  F01D5/28 ,  F01D5/30

    Abstract: A composite blade assembly and a method of assembling a composite blade are provided. The composite blade assembly includes a composite blade having a radially inner root. A composite blade assembly includes a first platform and a circumferentially adjacent second platform abutting the first platform at a platform joint. Each of the first platform and the second platform includes a radially outer surface and a radially inwardly extending attachment member. The platform joint includes a slot extending through adjacent edges of the first platform and the second platform. The slot is configured to receive the radially inner root and the radially inner root is configured to be sandwiched between the attachment members. The blade assembly includes an adhesive system configured to join the radially inner root of the composite blade and the attachment members into a unitary structure, and a retaining clip configured to bias the attachment members towards each other.

    Rotor assembly for use in a turbofan engine and method of assembling
    277.
    发明授权
    Rotor assembly for use in a turbofan engine and method of assembling 有权

    公开(公告)号：US10125619B2

    公开(公告)日：2018-11-13

    申请号：US14945670

    申请日：2015-11-19

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray ,  Todd Alan Anderson

    IPC: F01D5/28 ,  F01D5/30

    Abstract: A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a blade opening defined therein, and a rotor blade radially insertable through the blade opening. The rotor blade includes a rotor blade radially insertable through the blade opening. The rotor blade includes a root portion having a dovetail shape, and the root portion is undersized relative to the blade opening. At least one secondary dovetail member is positioned within the blade opening and configured to couple the root portion within the blade opening with an interference fit.

    Rotor assembly for use in a turbofan engine and method of assembling
    278.
    发明授权
    Rotor assembly for use in a turbofan engine and method of assembling 有权

    公开(公告)号：US10047763B2

    公开(公告)日：2018-08-14

    申请号：US14968306

    申请日：2015-12-14

    Applicant: General Electric Company

    Inventor： Todd Alan Anderson ,  Nicholas Joseph Kray ,  Bryant Edward Walker

    IPC: F04D29/32 ,  F04D29/64 ,  F01D5/30

    Abstract: A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a first blade opening defined therein, a first rotor blade configured to be radially inserted through the first blade opening, and a fairing positioned on a radially outer side of the annular spool. The first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool. The fairing is configured to receive a fastener radially inserted through the flange portion and the annular spool such that the first rotor blade is secured to the annular spool.

    TURBOFAN CASE FOR CONTROLLING BLADE DEFLECTION
    279.
    发明申请
    TURBOFAN CASE FOR CONTROLLING BLADE DEFLECTION 审中-公开

    公开(公告)号：US20180202460A1

    公开(公告)日：2018-07-19

    申请号：US15405965

    申请日：2017-01-13

    Applicant: General Electric Company

    Inventor： Nicholas Joseph Kray

    IPC: F04D29/52 ,  F02K3/06 ,  F04D19/00 ,  F04D25/04 ,  F04D29/32 ,  F04D29/38

    Abstract: A containment structure configured to provide close tolerance for a rotation structure. The containment structure includes an annular inner casing having an inner annular surface being formed of an abradable material. The rotation structure is configured to be received within the annular inner casing such that the rotation structure is normally spaced-apart from the inner annular surface. The inner annular surface surrounds the rotation structure and has a first width. The rotation structure has a second width and the first width is greater than the second width. At least a section of the inner annular surface of the abradable material is cylindrical.

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