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    AIRFOIL AND METHOD FOR IMPROVING HEAT TRANSFER OF AIRFOIL
    1.
    发明专利
    AIRFOIL AND METHOD FOR IMPROVING HEAT TRANSFER OF AIRFOIL 审中-公开

    公开(公告)号：JP2003138905A

    公开(公告)日：2003-05-14

    申请号：JP2002269736

    申请日：2002-09-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  CHON YOUNG H ,  DUBE BRYAN P

    IPC: F01D5/18 ,  F01D9/02 ,  F02C7/18

    Abstract: PROBLEM TO BE SOLVED: To provide an airfoil having an improved cooling mechanism. SOLUTION: An airfoil part of a turbine includes internal cavities 52, 54 and a plurality of indentations 90 disposed on inside surfaces 38 of the internal cavities. By the dents 90, heat transfer is improved to cool the internal cavities 52, 54 of the airfoil to elongate the service life of the airfoil, and the amount of compressor bleed air required is reduced to optimize engine efficiency. The advantage of such a cooling mechanism is that it does not restrict a cooling flow in the internal cavities 52, 54. The indentations 90 may have variable patterns or different geometric shapes.

    METHOD FOR FORMING MATERIAL ON FLOW ORIENTATION ASSEMBLY SURFACE FOR GAS TURBINE ENGINE
    3.
    发明专利
    METHOD FOR FORMING MATERIAL ON FLOW ORIENTATION ASSEMBLY SURFACE FOR GAS TURBINE ENGINE 失效

    公开(公告)号：JPH11218001A

    公开(公告)日：1999-08-10

    申请号：JP31849998

    申请日：1998-11-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ITTLESON ALAN J ,  DUBE BRYAN P ,  JOHNSON JEFFREY B ,  BAYER JEFFREY J

    IPC: F01D5/20 ,  B23K9/04 ,  B23K9/173

    Abstract: PROBLEM TO BE SOLVED: To unnecessitate finishing working for a passage surface of a shroud by melting a hard surface forming material on a notch surface, pressing a metallic pat on the lower side surface of the shroud and preventing the molten material from flowing to the lower side surface of the shroud. SOLUTION: In a shroud 12 of a partially formed rotary blade 10, a base part is provided, a hard surface forming material is stored, the location of a notch surface is made apart from the base part in the horizontal direction and the hard surface forming material is added till the material extends beyond the location of the notch surface. A clamp 64 which extends in the horizontal direction and is provided with a pair of arms 66, 68 is mounted on a base 54 of a fixing tool 14 and the clamp 64 is connected with each side part 28, 32 of a platform area 26 of the rotary blade 10. A pat 48 of an assembly 52 is connected so as to compatible to a passage surface of the shroud 12 by an arm 128, a molten material is prevented from flowing to the passage surface of the shroud 12 and an extremely little material extends to the side surface of the shroud 12 after the pad 48 is used.

    TURBINE AIRFOIL PLATFORM PLATYPUS FOR LOW BUTTRESS STRESS
    8.
    发明专利
    TURBINE AIRFOIL PLATFORM PLATYPUS FOR LOW BUTTRESS STRESS 未知

    公开(公告)号：SG130114A1

    公开(公告)日：2007-03-20

    申请号：SG2006052211

    申请日：2006-08-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DUBE BRYAN P ,  BUTCHER RANDALL J

    Abstract: A blade is provided for use in a gas turbine engine. The blade has a platform, an airfoil portion extending radially from a first side of the platform, and an attachment portion extending from a second or underside side of the platform. The attachment portion includes a buttress which abuts the second side of the platform. The blade is provided with additional material on the second side of the platform for redistributing load away from the buttress.

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