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    Turbine engine with a shroud assembly
    1.
    发明授权
    Turbine engine with a shroud assembly 有权

    公开(公告)号：US12140035B2

    公开(公告)日：2024-11-12

    申请号：US17526313

    申请日：2021-11-15

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Paul Hadley Vitt ,  Andrew Breeze-Stringfellow

    IPC: F01D11/16 ,  F01D5/22 ,  F01D25/24

    Abstract: A shroud assembly for a turbine engine having a centerline axis. The shroud assembly having a shroud hanger, at least one shroud segment, and at least one biasing element extending between the two. The biasing element configured to radially bias the at least one shroud segment between an outboard position and an inboard position radially outward from the outboard position with respect to the centerline axis.

    Turbine engine with floating shrouds
    3.
    发明授权
    Turbine engine with floating shrouds 有权

    公开(公告)号：US11208912B2

    公开(公告)日：2021-12-28

    申请号：US16219059

    申请日：2018-12-13

    Applicant: General Electric Company

    Inventor： Paul Hadley Vitt ,  Andrew Breeze-Stringfellow

    IPC: F01D11/16 ,  F01D5/22 ,  F01D25/24

    Abstract: A shroud assembly for a gas turbine engine includes: at least one shroud hanger; an annular array of shroud segments carried by the child hanger at least one and arrayed about an engine centerline axis, each of the shroud segments having a flowpath side defining a portion of a primary engine flowpath, and an opposed backside facing the at least one shroud hanger, wherein the shroud segment is mounted to the at least one shroud hanger such that it is movable in a radial direction between an inboard position and an outboard position, in response to a balance of gas pressures prevailing on the flowpath side and the backside; and biasing means which urge each of the shroud segments towards one of the positions.

    COUNTER-ROTATING TURBINE
    6.
    发明公开
    COUNTER-ROTATING TURBINE 审中-公开

    公开(公告)号：US20230374935A1

    公开(公告)日：2023-11-23

    申请号：US17747497

    申请日：2022-05-18

    Applicant: General Electric Company ,  GE Avio S.r.l. ,  General Electric Deutschland Holding GmbH

    Inventor： Paul Hadley Vitt ,  Lyle Douglas Dailey ,  Matteo Renato Usseglio ,  Andreas Peters

    IPC: F02C3/067 ,  F02C6/00 ,  F02C7/36

    CPC classification number: F02C3/067 ,  F02C6/00 ,  F02C7/36 ,  F05D2220/76

    Abstract: A turbine section for a gas turbine engine defines a radial direction and includes a low-pressure (LP) turbine that includes a first plurality of LP turbine blades that includes a first stage having first stage LP turbine blades that rotate in a first direction at a first speed, a second plurality of LP turbine blades that includes a plurality of stages of LP turbine blades disposed downstream of the first stage LP turbine blades that rotate in a second direction opposite the first direction at a second speed, a first LP turbine spool connected to the first plurality of LP turbine blades on an inner side of the first plurality of LP turbine blades in the radial direction, and a second LP turbine spool connected to the second plurality of LP turbine blades on an inner side of the second plurality of LP turbine blades in the radial direction

    GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS
    7.
    发明申请
    GAS TURBINE ENGINES WITH HEAT RECOVERY SYSTEMS 有权

    公开(公告)号：US20220307418A1

    公开(公告)日：2022-09-29

    申请号：US17211345

    申请日：2021-03-24

    Applicant: General Electric Company ,  General Electric Deutschland Holding GmbH

    Inventor： Paul Hadley Vitt ,  Michael Simonetti ,  Ashish Sharma

    IPC: F02C7/141 ,  F01D25/12 ,  F02C7/16

    Abstract: A gas turbine engine includes a fan located at a forward portion of the gas turbine engine, a compressor section and a turbine section arranged in serial flow order. The compressor section and the turbine section together define a core airflow path. A rotary member is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. An outlet guide vane assembly includes multiple outlet guide vanes located in an exhaust airflow path downstream of the turbine section. The multiple outlet guide vanes being spaced-apart circumferentially from each other over an angular range of about 360 degrees, and each multiple outlet guide vane defining a radial extent. At least one of the multiple outlet guide vanes includes a cold fluid passageway extending at least partially radially therethrough through which a fluid coolant flows and another of the multiple guide vanes includes a heated fluid passageway extending at least partially radially therethrough through which the fluid coolant flows and receives heat from exhaust airflow from the core airflow path.

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