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    1.
    发明专利
    未知

    公开(公告)号：ES2105255T3

    公开(公告)日：1997-10-16

    申请号：ES93909511

    申请日：1993-04-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NIKKANEN JOHN P ,  BUBELLO ROBERT ,  MAIER GRANT P

    IPC: B64D15/04 ,  F02C7/047

    Abstract: An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

    2.
    发明专利
    未知

    公开(公告)号：DE69311876T2

    公开(公告)日：1998-02-12

    申请号：DE69311876

    申请日：1993-04-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NIKKANEN JOHN ,  BUBELLO ROBERT ,  MAIER GRANT

    IPC: B64D15/04 ,  F02C7/047

    Abstract: An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

    4.
    发明专利
    未知

    公开(公告)号：DE69311876D1

    公开(公告)日：1997-08-07

    申请号：DE69311876

    申请日：1993-04-13

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NIKKANEN JOHN ,  BUBELLO ROBERT ,  MAIER GRANT

    IPC: B64D15/04 ,  F02C7/047

    Abstract: An anti-icing system for a nacelle of a gas turbine powerplant is disclosed. Various construction details have been developed which provide means to exhaust fluid from an inlet shell cavity and into an external medium. In one embodiment, the exhaust means (62) includes a plurality of aerodynamically shaped vanes (66) disposed within the inlet shell cavity (52) and a plurality of exhaust slots (68) wherein each of the vanes is adjacent one of the exhaust slots. The vanes are adapted to turn a portion of the body of fluid flowing within the inlet shell cavity to a direction substantially normal to the direction of flow of the external medium.

    Cooling gas turbine engine component or region
    7.
    发明专利
    Cooling gas turbine engine component or region 未知

    公开(公告)号：GB2229496A

    公开(公告)日：1990-09-26

    申请号：GB9000107

    申请日：1990-01-03

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： REAM JEFFREY LYNN ,  BUBELLO ROBERT

    IPC: B64D29/00 ,  F02C7/14

    Abstract: A system for cooling a buffer region 66 in the nacelle 14 of a gas turbine engine after engine shutdown comprises providing cooling air to the region by blower means 74. The air is drawn from the by-pass duct 38 via opening 56 and conduit 62 through valve 82 to blower 74. The coolable components e.g. hydraulic fluid conduits (96, 98, 100, Fig. 2, not shown) are disposed in the region, a portion of the conduits at least being disposed in a shroud 72. … …

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