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    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART
    31.
    发明申请
    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINED PART 有权
    非线性电子放电加工部分

    公开(公告)号：US20140186164A1

    公开(公告)日：2014-07-03

    申请号：US13729286

    申请日：2012-12-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： James M. Koonankeil ,  Edward F. Pietraszkiewicz ,  Karl A. Schachtner ,  Kevin J. Klinefelter ,  Markus W. Fritch ,  Jason Daley

    IPC: F02C7/18 ,  B23H1/00

    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。

    MATE FACE ARRANGEMENT FOR GAS TURBINE ENGINE COMPONENTS
    32.
    发明申请
    MATE FACE ARRANGEMENT FOR GAS TURBINE ENGINE COMPONENTS 审中-公开

    公开(公告)号：US20200256195A1

    公开(公告)日：2020-08-13

    申请号：US16269793

    申请日：2019-02-07

    Applicant: United Technologies Corporation

    Inventor： Laengheng Khoun ,  Edward F. Pietraszkiewicz ,  David J. Hiskes

    IPC: F01D5/14 ,  F01D9/04 ,  F01D11/00 ,  F01D11/08

    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending in a radial direction from a platform, the airfoil section extending in an axial direction between an airfoil leading edge and an airfoil trailing edge, and the airfoil section extending in the circumferential direction between pressure and suction sides. The platform extends in the axial direction between a platform leading edge and a platform trailing edge, and extends in the circumferential direction between a first mate face and a second mate face. The platform has a radially facing surface joined with the airfoil section and has a cold side surface opposed to the radially facing surface. A first thickness is defined between the radially facing surface and the cold side surface adjacent the first mate face, and a second thickness is defined between the radially facing surface and the cold side surface adjacent the second mate face. The first thickness is greater than the second thickness from at least the airfoil leading edge to the airfoil trailing edge with respect to the axial direction. A method of assembly is also disclosed.

    PREFERENTIAL FLOW DISTRIBUTION FOR GAS TURBINE ENGINE COMPONENT
    33.
    发明申请
    PREFERENTIAL FLOW DISTRIBUTION FOR GAS TURBINE ENGINE COMPONENT 审中-公开

    公开(公告)号：US20200182464A1

    公开(公告)日：2020-06-11

    申请号：US16214824

    申请日：2018-12-10

    Applicant: United Technologies Corporation

    Inventor： Laengheng Khoun ,  Edward F. Pietraszkiewicz ,  Joshua E. Kinnaman

    IPC: F23R3/00 ,  F23R3/06 ,  F23R3/60

    Abstract: A combustor liner for a gas turbine engine according to an example of the present disclosure includes, among other things, at least one liner segment that has an external wall dimensioned to bound a combustion chamber. The external wall extends between leading and trailing edges in an axial direction and extends between opposed mate faces in a circumferential direction. A cooling circuit is defined by the external wall. A plurality of heat transfer features are distributed in the cooling circuit to define a first restricted flow region that tapers from the leading edge to the trailing edge and to define at least one prioritized flow region that extends substantially from the leading edge to the trailing edge such that the at least one prioritized flow region is bounded by a perimeter of the first restricted flow region, and the at least one prioritized flow region has a lesser concentration of the plurality of heat transfer features than the first restricted flow region.

    Low loss airflow port
    34.
    发明授权
    Low loss airflow port 有权

    公开(公告)号：US10273808B2

    公开(公告)日：2019-04-30

    申请号：US14938310

    申请日：2015-11-11

    Applicant: United Technologies Corporation

    Inventor： Brandon W. Spangler ,  Dominic J. Mongillo ,  Edward F. Pietraszkiewicz

    IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12

    Abstract: An airfoil of a gas turbine engine is provided. The airfoil includes an airfoil body having at least one internal flow passage, the body having a first surface and a second surface, the first surface defining a wall of the at least one internal flow passage and a bleed port fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice extending from the second surface toward the internal flow passage and a bleed port cavity extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.

    DUCTING PLATFORM COVER PLATE
    38.
    发明申请
    DUCTING PLATFORM COVER PLATE 有权
    导电平板盖板

    公开(公告)号：US20160047271A1

    公开(公告)日：2016-02-18

    申请号：US14924369

    申请日：2015-10-27

    Applicant: United Technologies Corporation

    Inventor： Pedro L. Castaneda ,  Edward F. Pietraszkiewicz ,  Rafael A. Perez ,  Nestor A. Alvarez ,  Seth J. Thomen

    IPC: F01D25/12 ,  F01D9/04

    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 may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge 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。 定子可以包括叶片平台。 管道板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。 导管板可以包括与叶片平台的前缘相邻的入口。 叶片平台可以包括与叶片平台的后缘相邻的出口。 导管板可以被配置成将冷却空气从前缘引导到后缘。

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