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    16.
    发明专利
    未知

    公开(公告)号：DE602005000449T2

    公开(公告)日：2007-08-23

    申请号：DE602005000449

    申请日：2005-03-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  SANTELER KEITH ,  GAYMAN SCOTT W ,  COUCH ERIC

    IPC: F01D5/00 ,  F01D5/18 ,  F01D5/08 ,  F02C7/16 ,  F02C7/18

    Abstract: A turbine airfoil includes a plurality of cooling circuits (22) embedded within the pressure and suction sidewalls (28,30) and a first and a second flow passage (32f,32g). The first flow passage (32f) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the pressure sidewall (28) and the second flow passage (32g) feeds the coolant fluid to the cooling circuits (22) that are embedded only within the suction sidewall (30).

    Microcircuit cooling for a turbine blade tip
    17.
    发明专利
    Microcircuit cooling for a turbine blade tip 未知

    公开(公告)号：SG127708A1

    公开(公告)日：2006-12-29

    申请号：SG200400363

    申请日：2004-01-28

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  DUBE BRYAN P

    IPC: F01D5/08 ,  F01D5/00 ,  F01D5/18 ,  F01D5/30 ,  F02C7/18

    Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes an embedded microcircuit that traverses a tip (36) between a suction sidewall (44) and a pressure sidewall (42) of the airfoil (54). The microcircuit includes at least one inlet (70) disposed proximate to the tip (36) and one of the sidewalls (44) for receiving cooling air from an internal cooling cavity of the airfoil and at least outlet (72) disposed proximate to the tip (36) through which the cooling air ejects into a region outside the airfoil.

    Airfoil trailing edge cooling
    18.
    发明专利
    Airfoil trailing edge cooling 未知

    公开(公告)号：SG126818A1

    公开(公告)日：2006-11-29

    申请号：SG200601050

    申请日：2006-02-17

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： ALBERT JASON E ,  CUNHA FRANK J

    Abstract: A turbine airfoil (13) includes a span wise extending cavity (35a) formed from a ceramic mold and a slot (34) extending from the cooling air cavity (35a) to a trailing edge (16) being formed by a refractory metal core (11). The refractory metal core (11) facilitates the reduction in the size of the slot (34) and also in the reduction in the size of pedestals (19, 21, 22, 23, 24, 26) which pass transversely through the slot (34) to interconnect the pressure side to the suction side of the airfoil (13). The blade has a cutback feature to expose a back surface (35) on the inner side of the suction side wall (33) with raised projections (41) being formed on the back surface (35) so as to enhance heat transfer characteristics thereof. Provision is made for fabricating the raised projections (41) by way of a photo etching process.

    Method and apparatus for cooling an airfoil
    19.
    发明专利
    Method and apparatus for cooling an airfoil 未知

    公开(公告)号：SG125938A1

    公开(公告)日：2006-10-30

    申请号：SG200401289

    申请日：2004-03-16

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  PALUMBO MICHAEL A

    IPC: F01D5/00 ,  F01D5/18

    Abstract: An improved cooling design and method for cooling airfoils within a gas turbine engine is provided which includes a plenum (80) longitudinally located within the leading edge (46) of the airfoils. Within the plenum (80) are positioned a plurality of turbulence promoters (86) to provide enhanced heat transfer within the leading edge (46). Also, the cooling design includes a plurality of inlets (72,76) to receive cooling air from an internal cavity (36) of the airfoil as well as a plurality of outlets (64,66) located within a trench on the exterior surface of the leading edge (46) through which the cooling air exists to film cool the leading edge.

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