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    RIM DRIVEN THRUSTER WITH ADJUSTABLE ROTOR BLADE PITCH
    3.
    发明申请
    RIM DRIVEN THRUSTER WITH ADJUSTABLE ROTOR BLADE PITCH 有权

    公开(公告)号：US20230074750A1

    公开(公告)日：2023-03-09

    申请号：US17890162

    申请日：2022-08-17

    Applicant: Peter Jacques Muller

    Inventor： Peter Jacques Muller

    IPC: F01D7/00 ,  F01D17/02 ,  F01D5/03

    Abstract: Flow control system systems and techniques are described. A flow control system, such as a thruster, includes an annular rotor within an annular housing. The annular rotor rotates about a central axis relative to the annular housing. The flow control system includes rotor blades with respective bases that are coupled to the annular rotor, and with respective tips directed toward the central axis. The flow control system includes a first actuator that rotates the annular rotor about the central axis relative to the annular housing, thus also rotating the rotor blades about the central axis relative to the annular housing. The flow control system includes a second actuator that rotates the rotor blades relative to the annular rotor. Actuation of the second actuator rotates a rotor blade about a rotor blade axis that extends from a base of the rotor blade toward the central axis.

    Counter rotating power turbine with reduction gearbox
    4.
    发明授权
    Counter rotating power turbine with reduction gearbox 有权

    公开(公告)号：US11105200B2

    公开(公告)日：2021-08-31

    申请号：US15648867

    申请日：2017-07-13

    Applicant: General Electric Company

    Inventor： Jeffrey Donald Clements ,  Darek Tomasz Zatorski ,  Brandon Wayne Miller ,  Joseph Robert Dickman

    IPC: F01D1/26 ,  F01D5/06 ,  F01D15/12 ,  F01D25/28 ,  F01D5/03 ,  F02C7/36 ,  F02C3/10 ,  F02C3/107

    Abstract: The present disclosure is directed to a turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction. The turbine engine includes a power turbine including a first turbine rotor assembly interdigitated with a second turbine rotor assembly along the longitudinal direction; a gear assembly coupled to the first turbine rotor assembly and the second turbine rotor assembly, wherein the gear assembly includes a first input interface coupled to the first turbine rotor assembly, a second input interface coupled to the second turbine rotor assembly, and one or more third gears coupled to the first input interface and the second input interface therebetween; and a first output shaft and a second output shaft, wherein each of the first output shaft and the second output shaft are configured to couple to an electrical load device.

    Counter rotating turbine with reversing reduction gear assembly
    5.
    发明授权
    Counter rotating turbine with reversing reduction gear assembly 有权

    公开(公告)号：US10801442B2

    公开(公告)日：2020-10-13

    申请号：US15427340

    申请日：2017-02-08

    Applicant: General Electric Company

    Inventor： Jeffrey Donald Clements ,  Darek Tomasz Zatorski ,  Alan Roy Stuart

    IPC: F02C7/36 ,  F02K3/072 ,  F02K3/06 ,  F01D1/26 ,  F02C3/107 ,  F01D5/03 ,  F02C3/067 ,  F01D1/24

    Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section and a gear assembly within or downstream of the turbine section. The turbine section includes a first rotating component and a second rotating component along the longitudinal direction. The first rotating component includes one or more connecting airfoils coupled to a radially extended rotor, and the second rotating component includes an inner shroud defining a plurality of inner shroud airfoils extended outward of the inner shroud along the radial direction. The second rotating component is coupled to a second shaft connected to an input accessory of the gear assembly, and the first rotating component is coupled to an output accessory of the gear assembly. The output accessory rotates the first rotating component about the axial centerline at a first speed and wherein the second rotating component rotates about the axial centerline at a second speed.

    TWO SPOOL GAS TURBINE ENGINE WITH INTERDIGITATED TURBINE SECTION
    7.
    发明申请
    TWO SPOOL GAS TURBINE ENGINE WITH INTERDIGITATED TURBINE SECTION 审中-公开

    公开(公告)号：US20180274365A1

    公开(公告)日：2018-09-27

    申请号：US15412157

    申请日：2017-01-23

    Applicant: General Electric Company

    Inventor： Alan Roy Stuart ,  Jeffrey Donald Clements ,  Richard Schmidt ,  Thomas Ory Moniz

    IPC: F01D1/26 ,  F01D5/03 ,  F01D5/06 ,  F02K3/06

    Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction, and a circumferential direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a turbine section that includes a first rotating component and a second rotating component. The first rotating component includes an inner shroud and an outer shroud outward of the inner shroud in the radial direction. The outer shroud defines a plurality of outer shroud airfoils extended inward of the outer shroud along the radial direction. The first rotating component further includes at least one connecting airfoil coupling the inner shroud and the outer shroud. The second rotating component is upstream of the one or more connecting airfoils of the first rotating component along the longitudinal direction. The second rotating component includes a plurality of second airfoils extended outward in the radial direction. The first rotating component defines at least one stage of the plurality of outer shroud airfoils upstream of the second rotating component.

    Inlet guide vane inner air seal surge retaining mechanism
    8.
    发明授权
    Inlet guide vane inner air seal surge retaining mechanism 有权
    进气导叶内空气密封浪涌保持机构

    公开(公告)号：US07854586B2

    公开(公告)日：2010-12-21

    申请号：US11809150

    申请日：2007-05-31

    Applicant: Daniel W. Major ,  Edward Torres

    Inventor： Daniel W. Major ,  Edward Torres

    IPC: F01D5/03 ,  F01D11/00

    CPC classification number: F01D17/162 ,  F01D11/001 ,  F01D11/127 ,  F01D25/246 ,  F05D2240/11 ,  F05D2240/55 ,  F05D2260/30 ,  F05D2270/101

    Abstract: An inner air seal carrier for use in a gas turbine engine having an inlet guide vane surge retainer comprises a body, a stationary sealing element and an outcropping. The body secures around an inlet guide vane inner diameter shroud. The stationary sealing element is disposed on a radially inward face of the body for engaging with a rotatable sealing element of a compressor rotor. The outcropping is positioned on the radially inward face of the body forward of the stationary sealing element for engaging with the surge retainer.

    Abstract translation: 用于具有入口导向叶片浪涌保持器的燃气涡轮发动机中的内部空气密封载体包括主体，固定密封元件和露头。 身体围绕入口导向叶片内径护罩固定。 固定密封元件设置在主体的径向向内的表面上，用于与压缩机转子的可旋转的密封元件接合。 露头位于固定密封元件前方的径向内侧面上，用于与浪涌保持器接合。

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