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    31.
    发明专利
    未知

    公开(公告)号：DE69930916T2

    公开(公告)日：2006-08-31

    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.

    32.
    发明专利
    未知

    公开(公告)号：DE60025074T2

    公开(公告)日：2006-06-29

    申请号：DE60025074

    申请日：2000-06-23

    Applicant: UNITED TECHNOLOGIES CORP

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

    COOLED BLADES FOR A GAS TURBINE ENGINE
    33.
    发明专利
    COOLED BLADES FOR A GAS TURBINE ENGINE 未知

    公开(公告)号：CA2007632C

    公开(公告)日：2000-03-14

    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 internally air cooled turbine blade for a gas turbine engine of the type including a trailing edge section, leading edge section and mid chord section wherein each section includes a straight through radial passage communicating cooling air from the root to the tip of the blade, and the radial passages (feed channels) on the pressure side and suction side supply the cooling air to the film cooling holes in the airfoil surface and the radial passage (feed chamber) in the mid chord section replenishes the feed channels with cooling air through replenishment cooling holes interconnecting the feed channels and feed chamber. The rotation of the blade imparts a centrifugal pumping action to the air within the feed chamber for maximizing the cooling effectiveness of the cooling air. The air discharging at the tip cools the tip of the blade and provides tip aerodynamic sealing and the leading edge and trailing edge are similarly fed cooling air.

    34.
    发明专利
    未知

    公开(公告)号：NO306739B1

    公开(公告)日：1999-12-13

    申请号：NO900803

    申请日：1990-02-20

    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.

    Internally air cooled turbine blade
    35.
    发明专利
    Internally air cooled turbine blade 未知

    公开(公告)号：DE4003803A1

    公开(公告)日：1998-01-08

    申请号：DE4003803

    申请日：1990-02-08

    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.

    38.
    发明专利
    未知

    公开(公告)号：DE60041025D1

    公开(公告)日：2009-01-22

    申请号：DE60041025

    申请日：2000-10-05

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KVASNAK WILLIAM S ,  LAFLEUR RONALD S ,  MOROSO JOE ,  SOECHTING FRIEDRICH O ,  JOE CHRISTOPHER R ,  HAYES DOUGLAS A

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

    Abstract: A cooling circuit 22 disposed between a first wall portion 36 and a second wall portion 38 of a wall 24 for use in a gas turbine engine, comprises one or more inlet apertures 40, and one or more exit apertures 44. The inlet aperture(s) 40 provides a cooling airflow path into the cooling circuit 22 and the exit aperture(s) 44 provides a cooling airflow path out of the cooling circuit 22. The cooling circuit includes a plurality of first pedestals 34 extending between the first wall portion 36 and the second wall portion 38. The first pedestals 34 arc arranged in one or more rows 48. Preferably the distance between the pedestals 34 in a row 48 is greater than the distance between the rows 48. Also, preferably the passage 57, 90 between the pedestals 34 define a pair of throats 62, 64 with a diffuser 60 in between. The exit apertures 44 are preferably defined between a plurality of second and third pedestals 66, 68 with mating geometries.

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