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    METHOD AND DEVICE FOR FEEDING COOLING AIR FLOW TO TURBINE ENGINE
    1.
    发明专利
    METHOD AND DEVICE FOR FEEDING COOLING AIR FLOW TO TURBINE ENGINE 失效

    公开(公告)号：JP2002054459A

    公开(公告)日：2002-02-20

    申请号：JP2001140808

    申请日：2001-05-11

    Applicant: GEN ELECTRIC

    Inventor： WALLACE THOMAS TRACY ,  GLYNN CHRISTOPHER CHARLES ,  SHELTON MONTY LEE ,  CLEMENTS JEFFREY DONALD ,  LENAHAN DEAN T ,  KALB BARRY JOHN

    IPC: F02C7/18 ,  F01D5/08

    Abstract: PROBLEM TO BE SOLVED: To provide a method and device for directing air flow to a compressor bore. SOLUTION: A gas turbine rotor assembly contains a plurality of aerodynamic devices to direct a flow of air to the inside in a radial direction. The gas turbine engine rotor assembly contains a rotor shaft having a plurality of openings. An aerodynamic device contains a pair of blade segments and a pair of side walls. An outside surface having a contour shape contains an opening and the aerodynamic device can be installed in a manner to make contact with the inside surface of the rotor shaft and a flange ring demarcates a pocket. The aerodynamic device is fitted in the inside of the pocket with the openings adjusted to concentricity.

    3.
    发明专利
    未知

    公开(公告)号：BR0101964A

    公开(公告)日：2002-03-05

    申请号：BR0101964

    申请日：2001-05-14

    Applicant: GEN ELECTRIC

    Inventor： WALLACE THOMAS TRACY ,  GLYNN CHRISTOPHER CHARLES ,  SHELTON MONTY LEE ,  CLEMENTS JEFFREY DONALD ,  LENAHAN DEAN THOMAS ,  KALB BARRY JOHN

    IPC: F02C7/18 ,  F01D5/08

    Abstract: A gas turbine engine rotor assembly includes a plurality of aerodynamic devices (66) to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft (44) that includes a plurality of openings (52). The aerodynamic devices include a pair of vane segments (140) and a pair of sidewalls (142). A contoured outer surface (132) includes an opening (74) and permits the aerodynamic device to be positioned against an inner surface (50) of the rotor shaft, and a flange ring (60, 64) defines a pocket (65). The aerodynamic device fits within the pocket to concentrically align the openings (52,74).

    PROCEDIMIENTO Y APARATO PARA SUMINISTRAR AIRE DE REFRIGERACION A ROTORES DE TURBINAS.
    4.
    发明专利
    PROCEDIMIENTO Y APARATO PARA SUMINISTRAR AIRE DE REFRIGERACION A ROTORES DE TURBINAS. 未知

    公开(公告)号：ES2288499T3

    公开(公告)日：2008-01-16

    申请号：ES01304245

    申请日：2001-05-11

    Applicant: GEN ELECTRIC

    Inventor： WALLACE THOMAS TRACY ,  SHELTON MONTY LEE ,  LENAHAN DEAN THOMAS ,  GLYNN CHRISTOPHER CHARLES ,  CLEMENTS JEFFREY DONALD ,  KALB BARRY JOHN

    IPC: F01D5/08 ,  F02C7/18

    Abstract: Un conjunto (42) de rotor para un motor (10) de turbina de gas, comprendiendo dicho conjunto de rotor un árbol (44) de rotor que comprende una superficie (50) interior y una superficie (48) exterior; comprendiendo además el árbol de rotor una pluralidad de primeras aberturas (52) que se extienden entre la superficie (50) interior y la superficie (48) exterior; y, una pluralidad de dispositivos (66) aerodinámicos que se extienden de manera circunferencial dentro de dicho árbol de rotor y configurados para redirigir flujo (70) de aire a través de dicho árbol (44) de rotor, caracterizado porque cada uno de dichos dispositivos aerodinámicos comprende una segunda abertura (74) que se extiende a través de los mismos alineada de manera circunferencial con dicha primera abertura y que puede moverse de manera radial dentro del árbol (44) de rotor durante la rotación de dicho árbol de rotor.

    5.
    发明专利
    未知

    公开(公告)号：DE60129382D1

    公开(公告)日：2007-08-30

    申请号：DE60129382

    申请日：2001-05-11

    Applicant: GEN ELECTRIC

    Inventor： WALLACE THOMAS TRACY ,  SHELTON MONTY LEE ,  LENAHAN DEAN THOMAS ,  GLYNN CHRISTOPHER CHARLES ,  CLEMENTS JEFFREY DONALD ,  KALB BARRY JOHN

    IPC: F01D5/08 ,  F02C7/18

    Abstract: A gas turbine engine rotor assembly includes a plurality of aerodynamic devices (66) to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft (44) that includes a plurality of openings (52). The aerodynamic devices include a pair of vane segments (140) and a pair of sidewalls (142). A contoured outer surface (132) includes an opening (74) and permits the aerodynamic device to be positioned against an inner surface (50) of the rotor shaft, and a flange ring (60, 64) defines a pocket (65). The aerodynamic device fits within the pocket to concentrically align the openings (52,74).

    6.
    发明专利
    未知

    公开(公告)号：DE60129382T2

    公开(公告)日：2008-03-20

    申请号：DE60129382

    申请日：2001-05-11

    Applicant: GEN ELECTRIC

    Inventor： WALLACE THOMAS TRACY ,  SHELTON MONTY LEE ,  LENAHAN DEAN THOMAS ,  GLYNN CHRISTOPHER CHARLES ,  CLEMENTS JEFFREY DONALD ,  KALB BARRY JOHN

    IPC: F01D5/08 ,  F02C7/18

    Abstract: A gas turbine engine rotor assembly includes a plurality of aerodynamic devices (66) to direct airflow radially inward. The gas turbine engine rotor assembly includes a rotor shaft (44) that includes a plurality of openings (52). The aerodynamic devices include a pair of vane segments (140) and a pair of sidewalls (142). A contoured outer surface (132) includes an opening (74) and permits the aerodynamic device to be positioned against an inner surface (50) of the rotor shaft, and a flange ring (60, 64) defines a pocket (65). The aerodynamic device fits within the pocket to concentrically align the openings (52,74).

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