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    HOLLOW AIRFOIL
    1.
    发明专利
    HOLLOW AIRFOIL 失效

    公开(公告)号：JP2001164902A

    公开(公告)日：2001-06-19

    申请号：JP37577898

    申请日：1998-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： MARTIN G TABITA ,  JAMES P DOWNES ,  SOECHTING FRIEDRICH O ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D9/02

    Abstract: PROBLEM TO BE SOLVED: To provide a device to perform proper cooling along the front edge of a hollow airfoil, have a position adapted for a variable stagnation line, generate a cooling airfilm, having uniformity and permanency, in a position situated downstream from the front edges on the two side part of the airfoil and further, minimize a stress generating at the wall of the airfoil. SOLUTION: A hollow airfoil 16 comprises a body; a trench 18; and a plurality of cooling holes 38 formed in the trench. The body is extended in the direction of a chord between a front edge 26 and a rear edge and extended in the direction of a span between an outside radial surface and an inside radial direction and contains an external wall 24 to surround a cavity 22. A trench 18 is situated at an external wall 24 along the front edge 26 and extended in the direction of a span, and aligned with a stagnation line (a stagnation point 42) extending along the front edge 26.

    BYPASS AIR VALVE FOR TURBO FAN GAS TURBINE ENGINE
    2.
    发明专利
    BYPASS AIR VALVE FOR TURBO FAN GAS TURBINE ENGINE 失效

    公开(公告)号：JPH10325364A

    公开(公告)日：1998-12-08

    申请号：JP15531498

    申请日：1998-05-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： NARCUS ANDREW R ,  HAYES DOUGLAS A ,  AUXIER THOMAS A

    IPC: F02K3/06 ,  F01D17/10 ,  F02C9/18 ,  F02K3/075 ,  F02K3/077 ,  F02K3/10

    Abstract: PROBLEM TO BE SOLVED: To improve efficiency by suppressing work quantity of work lost for cooling to minimum. SOLUTION: A bypass air valve 20 has a liner 36 and a strap 34. The liner 36 has a plurality of first regions 46 and second regions 48. Each first region 46 has a plurality of first openings 52. Each second region 48 has a plurality of second openings 56. The strap 34 has a plurality of openings 78 and third regions 76. Each third region 76 has a plurality of third openings 80. When the valve is opened, the first region 46 is arranged in line with the opening 78. In addition, the third region 76 is arranged substantially in line with the second region 48. When the valve is closed, the first region 46 is arranged substantially in line with the third region 76, while the second region 48 is arranged in line with the opening 78.

    AIR FOIL
    5.
    发明专利
    AIR FOIL 失效

    公开(公告)号：JP2001020703A

    公开(公告)日：2001-01-23

    申请号：JP2000188966

    申请日：2000-06-23

    Applicant: UNITED TECHNOLOGIES CORP

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

    IPC: F01D5/18 ,  F01D9/02

    Abstract: PROBLEM TO BE SOLVED: To provide a method and device for cooling a rotor blade wall by utilizing a smaller amount of cooling air than in conventional cooling methods and devices. SOLUTION: This method for cooling a wall 12 of a rotor blade 21 includes a step for providing the wall 12 having inner and outer faces, a step for disposing in the wall 12 a cooling micro circuit 10 with a passage for cooling air extending between the inner and outer faces, and a step for enhancing heat transfer to a fluid from the wall 12 to the passage by increasing an average heat transfer coefficient per unit flow rate in the micro circuit 10. This method and device can be adjusted so as to substantially coincide with a thermal profile of the wall 10 at that place.

    HOLLOW AIR FOIL
    6.
    发明专利
    HOLLOW AIR FOIL 失效

    公开(公告)号：JPH11247611A

    公开(公告)日：1999-09-14

    申请号：JP37577998

    申请日：1998-12-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LIANG GEORGE P ,  AUXIER THOMAS A

    IPC: F01D5/18 ,  F01D9/02

    Abstract: PROBLEM TO BE SOLVED: To provide an appropriate cooling along a leading edge of a hollow air foil, generate a uniform and perpetual cooling air film downstream of the leading edge on both sides of the air foil, and minimize a stress generated in a wall of the air foil. SOLUTION: The hollow air foil comprises a main body, a trench 30, and a plurality of cooling hole 36 provided to the trench 30. The main body includes an outer wall 22 extending in a blade chord direction between a leading edge 24 and a trailing edge, extending in a span direction between an outer radius direction surface and an inner radius direction surface, and surrounding a cavity 20. The trench 30 is provided to the outer wall 22 along the leading edge 24, and extends in the span direction.

    7.
    发明专利
    未知

    公开(公告)号：DE19502998B4

    公开(公告)日：2005-03-03

    申请号：DE19502998

    申请日：1995-01-31

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SOECHTING FRIEDRICH O ,  AUXIER THOMAS A

    IPC: F01D5/18

    Abstract: The airfoil comprises of a leading edge (18) and a trailing edge (20) that is located downstream of a compressor airflow. The air is directed into internal chambers (55.56) within the airfoil and out through ports located along the pressure side of the airfoil between leading and trailing edges to form a cooling airflow. An additional film cooling hole (66) is located near the trailing edge of the airfoil. The film cooling hole admits an additional airflow into high and low pressure chambers (60,64) that are downstream of the initial internal airfoil flow. The two chambers are in communication via a passage (62). This creates a pressure drop in the downstream direction of the internal flow that causes the airflow from the exit (34) to adhere the pressure side of the airfoil thus producing a boundary layer airflow along the pressure side.

    Internally air cooled turbine blade
    8.
    发明专利
    Internally air cooled turbine blade 未知

    公开(公告)号：FR2798422A1

    公开(公告)日：2001-03-16

    申请号：FR9000792

    申请日：1990-01-24

    Applicant: UNITED TECHNOLOGIES CORP

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

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

    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
    9.
    发明专利
    COOLED BLADES FOR A GAS TURBINE ENGINE 未知

    公开(公告)号：CA2007631C

    公开(公告)日：2000-03-14

    申请号：CA2007631

    申请日：1990-01-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HALL KENNETH B ,  MCCLELLAND ROBERT J ,  AUXIER THOMAS A

    IPC: F01D5/18

    Abstract: An internally cooled turbine blade for a gas turbine engine is modified at the leading and trailing edges to include a dynamic cool air flowing radial passageway with an inlet at the root and a discharge at the tip feeding a plurality of radially spaced film cooling holes in the airfoil surface. Replenishment holes communicating with the serpentine passages radially spaced in the inner wall of the radial passage replenish the cooling air lost to the film cooling holes. The discharge orifice is sized to match the backflow margin to achieve a constant film hole coverage throughout the radial length. Trip strips may be employed to augment the pressure drop distribution

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