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    FINNED SEAL ASSEMBLY FOR GAS TURBINE ENGINES
    1.
    发明申请
    FINNED SEAL ASSEMBLY FOR GAS TURBINE ENGINES 有权
    用于气体涡轮发动机的精密密封组件

    公开(公告)号：US20140003919A1

    公开(公告)日：2014-01-02

    申请号：US13534060

    申请日：2012-06-27

    Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    IPC: F01D11/00

    CPC classification number: F01D11/001

    Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

    Abstract translation: 设置在涡轮发动机中的热气体路径和盘腔之间的密封组件包括从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片 从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。 翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。 在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中 密封组装。

    Nose bullet anti-icing for gas turbine engines
    2.
    发明授权
    Nose bullet anti-icing for gas turbine engines 失效
    燃气涡轮发动机的鼻子防弹结冰

    公开(公告)号：US4941317A

    公开(公告)日：1990-07-17

    申请号：US337468

    申请日：1989-04-13

    Applicant: Paul C. Ivey ,  John M. Owen

    Inventor： Paul C. Ivey ,  John M. Owen

    IPC: F01D5/08 ,  F01D25/02 ,  F02C7/047

    CPC classification number: F02C7/047 ,  F01D25/02 ,  F01D5/085 ,  F05D2260/209

    Abstract: A flow inducing means 110 for use in an anti-icing system for a nose bullet 10 of a gas turbine engine of the type in which hot gas is caused to flow along the center of a rotating tube 7,62 towards the nose bullet 10 to heat it, and cooled air is centrifuged to the surface of the bore of the tube 7,62 and is displaced rearwardly along the tube. The tube 7,62 is open at its rear end, and the flow inducing means 110 is positioned adjacent the open end. The flow inducing means 110 comprises a plurality of radial vanes 111 which enters in a radially inwards direction and the vanes 111 are shaped and positioned to redirect the gas axially along the center of the tube 7. The flow inducer 110 may include a shroud 115 which has a circumferential inlet opening and an axial facing outlet 116. The shroud may serve as a flow separator which separates the incoming hot gas from the cooled gas exiting the tube.

    Abstract translation: 一种用于燃气涡轮发动机的鼻子10的防冰系统的流动诱导装置110，其中使热气体沿着旋转管7,62的中心朝向鼻子弹簧10流动， 加热，并将冷却的空气离心到管7,62的孔的表面，并沿着管向后移位。 管7,62在其后端开口，并且流动诱导装置110位于开口端附近。 流动诱导装置110包括多个径向向内进入的径向叶片111，并且叶片111成形并定位成沿着管7的中心轴向地重新定向气体。流动诱导器110可包括护罩115，护罩115 具有圆周入口开口和面向轴向的出口116.护罩可以用作将进入的热气体与离开管的冷却气体分离的流动分离器。

    Finned seal assembly for gas turbine engines
    5.
    发明授权
    Finned seal assembly for gas turbine engines 有权
    燃气涡轮发动机的翅片密封组件

    公开(公告)号：US09121298B2

    公开(公告)日：2015-09-01

    申请号：US13534060

    申请日：2012-06-27

    Applicant: Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    Inventor： Ching-Pang Lee ,  Kok-Mun Tham ,  John M. Owen ,  Gary D. Lock ,  Carl M. Sangan ,  Vincent P. Laurello

    IPC: F04D11/00 ,  F01D11/00

    CPC classification number: F01D11/001

    Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

    Abstract translation: 设置在涡轮发动机中的热气体路径和盘腔之间的密封组件包括从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片 从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。 翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。 在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中 密封组装。

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