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    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE
    5.
    发明申请
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE 审中-公开
    燃气涡轮发动机SERPENTINE冷却通风

    公开(公告)号：WO2014042955A1

    公开(公告)日：2014-03-20

    申请号：PCT/US2013/058282

    申请日：2013-09-05

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： PEREZ, Rafel A. ,  PIETRASZKIEWICZ, Edward F. ,  LEVINE, Jeffrey R. ,  MONGILLO JR., Dominic J.

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

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/183 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141 ,  F05D2270/17 ,  Y02T50/673 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，该冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。 下游部分包括与内壁相对的外壁，以提供在内壁和外壁之间延伸的下游区域。 湍流促进剂从与下游部分中的弯曲部相邻的外壁延伸。 在与下游部分中的弯曲部相邻的内壁的停滞区域中不存在湍流促进剂

    DUCTING PLATFORM COVER PLATE
    6.
    发明申请
    DUCTING PLATFORM COVER PLATE 审中-公开
    导电平板盖板

    公开(公告)号：WO2015026430A1

    公开(公告)日：2015-02-26

    申请号：PCT/US2014/042976

    申请日：2014-06-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： THOMEN, Seth J. ,  CASTANEDA, Pedro L. ,  PIETRASZKIEWICZ, Edward F. ,  PEREZ, Rafael A. ,  ALVAREZ, Nestor A.

    IPC: F01D9/06

    CPC classification number: F01D25/12 ,  F01D9/041 ,  F01D9/065 ,  F05D2220/30 ,  F05D2240/81 ,  F05D2260/20 ,  F05D2260/202 ,  F05D2260/205 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: The present disclosure relates to cooling systems for turbine stators. A stator (200) may include a vane platform (210). A ducting plate (330) may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber (350) between the ducting plate and the vane platform. The ducting plate may include an inlet (340) adjacent to a leading edge (310) of the vane platform. The vane platform may include an outlet (360) adjacent to a trailing edge (320) of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.

    Abstract translation: 本公开涉及涡轮定子的冷却系统。 定子（200）可以包括叶片平台（210）。 管道板（330）可以联接到叶片平台。 导管板和叶片平台可以在管道板和叶片平台之间形成冷却室（350）。 导管板可以包括与叶片平台的前缘（310）相邻的入口（340）。 叶片平台可以包括与叶片平台的后缘（320）相邻的出口（360）。 导管板可以被配置成将冷却空气从前缘引导到后缘。

    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART
    8.
    发明申请
    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART 审中-公开
    非线性电子放电加工部分

    公开(公告)号：WO2014105393A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/073618

    申请日：2013-12-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： KOONANKEIL, James M. ,  PIETRASZKIEWICZ, Edward F. ,  SCHACHTNER, Karl A. ,  KLINEFELTER, Kevin J. ,  FRITCH, Markus W. ,  DALEY, Jason

    IPC: F01D5/18 ,  F02C7/18 ,  F01D25/12

    CPC classification number: B23H1/00 ,  B23H7/265 ,  B23H7/30 ,  B23H9/10 ,  F01D5/187 ,  F05D2230/12 ,  F05D2240/12 ,  F05D2240/81 ,  Y02T50/676 ,  Y10T29/49323 ,  Y10T29/49341

    Abstract: A method of machining cooling holes in a component includes the steps of inserting an electro discharge machining guide that houses an electrode into an internal cavity of a component, and machining a cooling hole into a wall of the component with the electrode. A gas turbine engine component includes first and second spaced apart walls providing an internal cavity. The first wall has outer and inner surfaces. The inner surface faces the internal cavity. A cooling hole extends through the first wall from the inner surface to the outer surface. The cooling hole includes entry and exit openings respectively provided in the inner and outer surfaces. The exit opening includes a cross-sectional area that is smaller than a cross-sectional area of the entry opening.

    Abstract translation: 在部件中加工冷却孔的方法包括以下步骤：将容纳电极的放电加工引导件插入部件的内部空腔中，并用电极将冷却孔加工到部件的壁中。 燃气涡轮发动机部件包括提供内腔的第一和第二隔开的壁。 第一个墙壁有外表面和内表面。 内表面面向内腔。 冷却孔从内表面到外表面延伸穿过第一壁。 冷却孔包括分别设置在内表面和外表面上的入口和出口。 出口开口包括比入口开口的横截面面积小的横截面面积。

    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS
    9.
    发明申请
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS 审中-公开
    燃气涡轮发动机SERPENTINE冷却通风与CHEVRONS

    公开(公告)号：WO2014105392A1

    公开(公告)日：2014-07-03

    申请号：PCT/US2013/073558

    申请日：2013-12-06

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： GOELLER, Travis ,  GRANSTRAND, Erik R. ,  SINGER, Irwin D. ,  MONGILLO, Dominic, J., Jr. ,  PIETRASZKIEWICZ, Edward F.

    IPC: F01D5/14 ,  F02C7/12 ,  F02K3/00

    CPC classification number: F01D5/188 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. First and second trip strips are respectively arranged in the upstream and downstream portions. The first trip strips are arranged at a first spacing from one another. The second trip strips are arranged at a second spacing from one another. A turbulence promoter is arranged in the bend and at a third spacing from the first trip strips that is different than the first spacing. The turbulence promoter is arranged at a fourth spacing from the second trip strips that is different than the second spacing.

    Abstract translation: 燃气涡轮发动机部件包括具有冷却通道的结构，该冷却通道提供通过内壁彼此分离并通过弯曲部流体连接的上游和下游部分。 第一和第二跳闸条分别布置在上游和下游部分中。 第一行程条以彼此之间的第一间距布置。 第二跳闸条以相互间隔开的第二间隔布置。 湍流促进器布置在弯曲中并且以与第一间隔不同的第一跳闸带的第三间隔布置。 湍流促进器被布置在与第二间隔不同的第二跳闸带的第四间隔处。

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