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    MANUFACTURABLE AND INSPECTABLE MICROCIRCUIT COOLING FOR BLADES
    3.
    发明专利
    MANUFACTURABLE AND INSPECTABLE MICROCIRCUIT COOLING FOR BLADES 未知

    公开(公告)号：CA2557233A1

    公开(公告)日：2007-02-28

    申请号：CA2557233

    申请日：2006-08-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： PIETRASZKIEWICZ EDWARD F ,  SHARMA OM PARKASH ,  CUNHA FRANK

    IPC: B22F5/04 ,  F01D5/18

    Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.

    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS
    5.
    发明专利
    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS 未知

    公开(公告)号：SG130130A1

    公开(公告)日：2007-03-20

    申请号：SG2006053573

    申请日：2006-08-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SHARMA OM PARKASH ,  CUNHA FRANK ,  PIETRASZKIEWICZ EDWARD F

    Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.

    MANUFACTURABLE AND INSPECTABLE MICROCIRCUIT COOLING FOR BLADES
    6.
    发明专利
    MANUFACTURABLE AND INSPECTABLE MICROCIRCUIT COOLING FOR BLADES 未知

    公开(公告)号：SG130131A1

    公开(公告)日：2007-03-20

    申请号：SG2006053581

    申请日：2006-08-07

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK ,  SHARMA OM PARKASH ,  PIETRASZKIEWICZ EDWARD F

    Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a plurality of microcircuits having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, and forming at least one additional cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion. Thereafter, the first half is placed in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected. The first half and the second half are joined together to form the airfoil portion.

    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS
    8.
    发明专利
    MANUFACTURABLE AND INSPECTABLE MICROCIRCUITS 未知

    公开(公告)号：CA2558479A1

    公开(公告)日：2007-02-28

    申请号：CA2558479

    申请日：2006-08-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SHARMA OM PARKASH ,  PIETRASZKIEWICZ EDWARD F ,  CUNHA FRANK

    IPC: B22F5/04 ,  F01D5/18 ,  F01D5/28

    Abstract: A method for manufacturing a turbine engine component comprises the steps of forming a first half of an airfoil portion of the turbine engine component and forming a first cooling microcircuit having at least one passageway on an exposed internal wall of the first half of the airfoil portion. The method further comprises forming a second half of the airfoil portion of said turbine engine component, forming a second cooling microcircuit having at least one passageway on an exposed internal wall of the second half of the airfoil portion, and placing the first half in an abutting relationship with the second half after the cooling microcircuits have been formed and inspected.

    MICRO-CIRCUIT PLATFORM
    9.
    发明专利
    MICRO-CIRCUIT PLATFORM 未知

    公开(公告)号：CA2495740A1

    公开(公告)日：2005-08-03

    申请号：CA2495740

    申请日：2005-02-01

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： TELLER BRET ,  CUNHA FRANK ,  SANTELER KEITH

    IPC: F01D5/14 ,  F01D5/18 ,  F02C7/18 ,  F01D5/30

    Abstract: A gas turbine engine component, such as a high pressure turbine blade, has an airfoil portion, a platform, and micro- circuits within the platform for cooling at least one of a platform edge adjacent the pressure side of the airfoil portion and the trailing edge of the platform. The micro- circuits include a first micro-circuit on a suction side of the airfoil and a second micro-circuit on a pressure side of the airfoil. The micro-circuits within the platform achieve high thermal connective efficiency, high film coverage, and high cooling effectiveness.

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