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    COOLED BLADES FOR A GAS TURBINE ENGINE
    21.
    发明专利
    COOLED BLADES FOR A GAS TURBINE ENGINE 未知

    公开(公告)号：CA2007632A1

    公开(公告)日：1997-06-06

    申请号：CA2007632

    申请日：1990-01-12

    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.

    23.
    发明专利
    未知

    公开(公告)号：DE69930916D1

    公开(公告)日：2006-05-24

    申请号：DE69930916

    申请日：1999-12-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TABBITA MARTIN G ,  DOWNS JAMES P ,  SOECHTING FRIEDRICH O

    IPC: F01D5/18 ,  F02C7/00

    Abstract: A hollow airfoil 16 is provided which includes a body having an external wall 22 and an internal cavity 20. The external wall 22 includes a suction side portion 28 and a pressure side portion 30. The portions extend chordwise between a leading edge 24 and a trailing edge 32 and spanwise between an inner radial surface 14 and an outer radial surface 18. A stagnation line 40 extends along the leading edge 24. A plurality of cooling apertures 26, are disposed spanwise along the leading edge 14. In one embodiment the apertures 26 coincide with the stagnation line 40 and extend through the external wall 22 along a helical path. The apertures 26 are alternately directed towards the suction side portion 28 and the pressure side portions 30 of the airfoil 16. The apertures 26 may open into a leading edge trench 34. In another embodiment (FIGS. 10 and 11) the apertures 26 are disposed on either side of the stagnation line 40.

    25.
    发明专利
    未知

    公开(公告)号：DE69613307T2

    公开(公告)日：2001-09-20

    申请号：DE69613307

    申请日：1996-10-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SOECHTING FRIEDRICH O ,  PLANK WILLIAM L ,  HALL KENNETH B

    IPC: F01D9/02 ,  F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C7/18

    Abstract: A vane assembly (14) for a gas turbine engine (12) includes a plurality of vanes (28), each having a forward compartment (44) and an aft compartment (46), an inner vane support (30), a casing (16), and apparatus (50,54) for maintaining a pressure difference between the compartments. The casing (16), which includes an annulus (18), is positioned radially outside of the vanes. The vanes (28) extend between the inner vane support (30) and the casing (16). The apparatus for maintaining a pressure difference may comprise a flow meter (50,54) at the entrance to the aft compartment. A modulating valve (22) may be provided to control the flow of cooling air into the annulus, and thus into the vanes.

    26.
    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.

    27.
    发明专利
    未知

    公开(公告)号：DE60041366D1

    公开(公告)日：2009-02-26

    申请号：DE60041366

    申请日：2000-06-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AUXIER THOMAS A ,  DOWNS JAMES P ,  CALHOUN WILLIAM H ,  KVASNAK WILLIAM S ,  SOECHTING FRIEDRICH O ,  HAYES DOUGLAS A

    IPC: F01D5/18 ,  F01D9/02

    Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

    30.
    发明专利
    未知

    公开(公告)号：DE60031185D1

    公开(公告)日：2006-11-16

    申请号：DE60031185

    申请日：2000-06-23

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： AUXIER THOMAS A ,  DOWNS JAMES P ,  CALHOUN WILLIAM H ,  KVASNAK WILLIAM S ,  SOECHTING FRIEDRICH O ,  HAYES DOUGLAS A

    IPC: F01D5/18 ,  F01D9/02

    Abstract: A method and apparatus for cooling a wall within a gas turbine engine is provided which comprises the steps of: (1) providing a wall having an internal surface and an external surface; (2) providing a cooling microcircuit within the wall that has a passage for cooling air that extends between the internal surface and the external surface; and (3) increasing heat transfer from the wall to a fluid flow within the passage by increasing the average heat transfer coefficient per unit flow within the microcircuit. According to one aspect, the present invention method and apparatus can be tuned to substantially match the thermal profile of the wall at hand.

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