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    Axial flow turbine for gas turbine engine
    11.
    发明专利
    Axial flow turbine for gas turbine engine 未知

    公开(公告)号：SE470600B

    公开(公告)日：1998-09-14

    申请号：SE9000113

    申请日：1990-01-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUBER FRANK W ,  DIETRICH DOUGLAS J

    IPC: F01D5/14 ,  F01D11/10 ,  F01D11/08

    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.

    12.
    发明专利
    未知

    公开(公告)号：SE9000236L

    公开(公告)日：1998-05-03

    申请号：SE9000236

    申请日：1990-01-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SELLERS ROBERT R ,  SOECHTING FRIEDRICH O ,  HUBER FRANK W ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D11/10

    Abstract: An axial flow turbine comprises a number of air cooled blades each of which have an airfoil surface exposed to the working medium defining a pressure side, a suction side, a root section, a tip section, and a mid chord section. Each blade having internal passages including at least one radial passage (26) defining a first feed channel adjacent the pressure side conducting cooling air from the root section to an outlet opening in the tip section, a number of radially spaced film cooling holes (28) in the airfoil surface being fed cool air from the feed channel, a second radial passage (32) defining a feed chamber in the mid chord section conducting cooling air from the root section to an orifice in the tip section, a number of radially spaced replenishment cooling holes communicating with the feed chamber for replenishing air in the feed channel whereby the rotation of the turbine centrifuges the air in the radial passages to increase the pressure of the cooling air as the air progresses toward the tip section of the blade.

    Cooled blades for a gas turbine engine
    16.
    发明专利
    Cooled blades for a gas turbine engine 未知

    公开(公告)号：AU684039B1

    公开(公告)日：1997-12-04

    申请号：AU4881490

    申请日：1990-01-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SELLERS ROBERT R ,  AUXIER THOMAS A ,  HUBER FRANK W ,  SOECHTING FRIEDRICH O

    IPC: F01D5/18 ,  F01D11/10

    Abstract: An axial flow turbine comprises a number of air cooled blades each of which have an airfoil surface exposed to the working medium defining a pressure side, a suction side, a root section, a tip section, and a mid chord section. Each blade having internal passages including at least one radial passage (26) defining a first feed channel adjacent the pressure side conducting cooling air from the root section to an outlet opening in the tip section, a number of radially spaced film cooling holes (28) in the airfoil surface being fed cool air from the feed channel, a second radial passage (32) defining a feed chamber in the mid chord section conducting cooling air from the root section to an orifice in the tip section, a number of radially spaced replenishment cooling holes communicating with the feed chamber for replenishing air in the feed channel whereby the rotation of the turbine centrifuges the air in the radial passages to increase the pressure of the cooling air as the air progresses toward the tip section of the blade.

    19.
    发明专利
    未知

    公开(公告)号：TR23587A

    公开(公告)日：1990-04-19

    申请号：TR20390

    申请日：1990-03-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SELLERS ROBERT R ,  SOECHTING FRIEDRICH O ,  HUBER FRANK W ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D11/10 ,  F02C ,  F01P

    Abstract: An axial flow turbine comprises a number of air cooled blades each of which have an airfoil surface exposed to the working medium defining a pressure side, a suction side, a root section, a tip section, and a mid chord section. Each blade having internal passages including at least one radial passage (26) defining a first feed channel adjacent the pressure side conducting cooling air from the root section to an outlet opening in the tip section, a number of radially spaced film cooling holes (28) in the airfoil surface being fed cool air from the feed channel, a second radial passage (32) defining a feed chamber in the mid chord section conducting cooling air from the root section to an orifice in the tip section, a number of radially spaced replenishment cooling holes communicating with the feed chamber for replenishing air in the feed channel whereby the rotation of the turbine centrifuges the air in the radial passages to increase the pressure of the cooling air as the air progresses toward the tip section of the blade.

    20.
    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.

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