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    EDM METHOD FOR MULTI-LOBED COOLING HOLE
    1.
    发明申请
    EDM METHOD FOR MULTI-LOBED COOLING HOLE 审中-公开
    多孔冷却孔的电火花加工方法

    公开(公告)号：WO2013165511A3

    公开(公告)日：2014-01-03

    申请号：PCT/US2013025716

    申请日：2013-02-12

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： LEVASSEUR GLENN ,  PIETRASZKIEWICZ EDWARD F ,  ZELESKY MARK F ,  MONGILLO DOMINIC J ,  KLINEFELTER KEVIN J ,  DOLL STEPHEN D ,  FRITCH MARKUS W

    IPC: F02C7/18 ,  F01D5/08 ,  F01D25/12 ,  F02K3/00

    CPC classification number: B23H9/10 ,  B23H1/00 ,  B23H7/26 ,  B23H9/14 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676

    Abstract: A method for forming a cooling hole extending from an inlet on a first surface of a wall to an outlet on a second surface of the wall includes forming a diffusing section of the cooling hole, and a trailing edge on the outlet by electrical discharge machining, and forming longitudinal lobes in the diffusing section. The metering section extends from the inlet on a first surface of the wall towards the second surface of the wall. The diffusing section extends from the outlet to one end of a metering section located between the inlet and the outlet. The outlet is substantially linear or convex at the trailing edge and the lobes are separated by longitudinal ridges.

    Abstract translation: 用于形成从壁的第一表面上的入口延伸到壁的第二表面上的出口的冷却孔的方法包括：通过放电加工形成冷却孔的扩散部分和出口上的后缘， 并在扩散段中形成纵向凸起。 计量部分从壁的第一表面上的入口延伸到壁的第二表面。 扩散部分从出口延伸到位于入口和出口之间的计量部分的一端。 出口在后缘处基本上是线性的或凸起的，并且叶片由纵向脊部分开。

    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES
    4.
    发明专利
    MISTAKE PROOF IDENTIFICATION FEATURE FOR TURBINE BLADES 未知

    公开(公告)号：SG130143A1

    公开(公告)日：2007-03-20

    申请号：SG2006054738

    申请日：2006-08-11

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： KANG MOON-KYOO BRIAN ,  LONCZAK KENNETH A ,  PIETRASZKIEWICZ EDWARD F

    Abstract: An identification feature is used to unmistakably identify internal features present in different generations of turbine blade designs. The identification feature is located on a root portion of the turbine blade and protrudes to provide a visually identifiable feature that is also readable by a coordinate measuring machine, but does not interfere with installation or operation of the turbine blade. The weight of the identification feature is in a specific proportion to the weight of the turbine blade in order to prevent interfere with operation of the turbine blade during high-speed rotation in a gas turbine engine.

    MANUFACTURABLE AND INSPECTABLE MICROCIRCUIT COOLING FOR BLADES
    5.
    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.

    Airfoil with three-pass serpentine cooling channeland microcircuit
    9.
    发明专利
    Airfoil with three-pass serpentine cooling channeland microcircuit 未知

    公开(公告)号：SG122040A1

    公开(公告)日：2006-05-26

    申请号：SG200508439

    申请日：2005-10-27

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  TELLER BRET ,  CHON YOUNG ,  MONGILLO DOMINIC ,  PIETRASZKIEWICZ EDWARD F

    Abstract: An airfoil (34), and in a disclosed embodiment a rotor blade, has a serpentine cooling path. To best account for the Coriolis effect, the paths of the serpentine cooling channel have trapezoidal cross-sections. An area of the rotor blade between a smaller side (43) of the trapezoidal-shaped paths, and a facing wall (46) of the rotor blade has high thermal and mechanical stresses, and is a challenge to adequately cool. A microcircuit (50), which is a very thin cooling circuit having crossing pedestals (112), is embedded into the blade in this area. The microcircuit provides additional cooling, and addresses the challenges with regard to cooling these areas.

    HEAT TRANSFERRING COOLING FEATURES FOR AN AIRFOIL
    10.
    发明专利
    HEAT TRANSFERRING COOLING FEATURES FOR AN AIRFOIL 未知

    公开(公告)号：CA2523630A1

    公开(公告)日：2006-05-09

    申请号：CA2523630

    申请日：2005-10-18

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： BOTNICK CHRISTINA ,  PIETRASZKIEWICZ EDWARD F ,  COONS TODD

    IPC: B64C3/36 ,  F28F3/12 ,  F28F13/12

    Abstract: A turbine blade airfoil assembly includes a cooling air passage. The cooli ng air passage includes a plurality of impingement openings that are isolated from at least one adjacent impingement opening. The cooling air passage is formed an d cast within a turbine blade assembly through the use of a single core. The single core forms the features required to fabricate the various separate and isolated impingement openings. The isolation and combination of impingement openings provides for the augmentation of convection and film cooling and provide the flexibility to tailor airflow on an airfoil to optimize thermal performance of an airfoil.

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