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    Axial flow turbine for gas turbine engine
    1.
    发明专利
    Axial flow turbine for gas turbine engine 未知

    公开(公告)号：FR2798423A1

    公开(公告)日：2001-03-16

    申请号：FR9000793

    申请日：1990-01-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

    IPC: F01D5/18 ,  F01D5/20 ,  F01D11/10 ,  F01D1/00

    Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

    Axial flow turbine for gas turbine engine
    2.
    发明专利
    Axial flow turbine for gas turbine engine 未知

    公开(公告)号：DE4003802A1

    公开(公告)日：1998-01-15

    申请号：DE4003802

    申请日：1990-02-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

    IPC: F01D5/14 ,  F01D5/18 ,  F01D11/10 ,  F02C7/18 ,  F02C7/28

    Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

    5.
    发明专利
    未知

    公开(公告)号：DE4003802C2

    公开(公告)日：2001-12-13

    申请号：DE4003802

    申请日：1990-02-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

    IPC: F01D5/14 ,  F01D5/18 ,  F01D11/10 ,  F02C7/18 ,  F02C7/28 ,  F01D5/20

    Abstract: An aerodynamic buffer zone in the gap between the tip of an air cooled axial flow turbine blade of a gas turbine engine and its surrounding shroud or seal (outer air seal) is created by discretely discharging a high velocity stream of cooling air from the tip of the blade in a judicious direction. The stream is angularly oriented relative to the plane of rotation of the turbine so that it is discharged in the gap in the direction of the pressure side of the turbine and preferably at between a 15 DEG -45 DEG angle relative to the flat surface of the tip of the blade.

    Axial flow turbine for gas turbine engine
    9.
    发明专利
    Axial flow turbine for gas turbine engine 未知

    公开(公告)号：DE4042729C2

    公开(公告)日：2002-10-31

    申请号：DE4042729

    申请日：1990-02-08

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

    IPC: F01D5/14 ,  F01D5/18 ,  F01D11/10 ,  F01D5/20

    Abstract: The axial flow turbine includes a number of internally air cooled turbine blades each having a tip section mounted adjacent the shroud and defining with it a gap that is susceptible of leaking engine working medium. Each internally cooled blade has an airfoil surface exposed to the engine working medium defining a pressure surface and a suction surface. A device minimises the leakage by providing a buffer zone in the gap. The device includes an orifice located in the tip section adjacent the pressure surface. The orifice is skewed relative to the rotation axis of the blade for leading air from internally of the blade into the gap toward the pressure side of the blades. The stream of air discharging from the orifice defines a buffer zone.

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