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    Cooling hole with crenellation features
    12.
    发明授权
    Cooling hole with crenellation features 有权
    冷却孔具有排气功能

    公开(公告)号：US08978390B2

    公开(公告)日：2015-03-17

    申请号：US14204465

    申请日：2014-03-11

    Applicant: United Technologies Corporation

    Inventor： Glenn Levasseur ,  Edward F. Pietraszkiewicz

    IPC: F01D5/18 ,  F04D31/00 ,  F02C7/12 ,  F01D25/14

    CPC classification number: F01D25/14 ,  F01D5/186 ,  F01D9/065 ,  F05D2240/81 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/324 ,  F05D2260/202 ,  F23R3/002 ,  F23R2900/03042 ,  Y02T50/676 ,  Y10T29/49229 ,  Y10T29/49323

    Abstract: A wall of a component of a gas turbine engine includes first and second wall surfaces, an inlet located at the first wall surface, an outlet located at the second surface, a metering section commencing at the inlet and extending downstream from the inlet, and a diffusing section extending from the metering section and terminating at the outlet. The diffusing section includes a leading edge formed at an upstream end of the outlet, a trailing edge formed at a downstream end of the outlet, a body region upstream of the trailing edge, and a plurality of crenellation features located on the body region.

    Abstract translation: 燃气涡轮发动机的部件的壁包括第一和第二壁表面，位于第一壁表面处的入口，位于第二表面处的出口，从入口开始并从入口的下游延伸的计量部分，以及 扩散部分从计量部分延伸并终止在出口处。 扩散部分包括形成在出口的上游端的前缘，形成在出口的下游端的后缘，在后缘的上游的身体区域，以及位于身体区域上的多个分类特征。

    Mate face arrangement for gas turbine engine components
    14.
    发明授权
    Mate face arrangement for gas turbine engine components 有权

    公开(公告)号：US11156098B2

    公开(公告)日：2021-10-26

    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.

    Blade platform gusset with internal cooling
    15.
    发明授权
    Blade platform gusset with internal cooling 有权

    公开(公告)号：US10677070B2

    公开(公告)日：2020-06-09

    申请号：US14886201

    申请日：2015-10-19

    Applicant: United Technologies Corporation

    Inventor： Joseph F. Englehart ,  Edward F. Pietraszkiewicz ,  Wieslaw A. Chlus ,  David M. Konopka ,  Luke A. Hmiel ,  Kenneth Boucher

    IPC: F02C1/00 ,  F01D5/18 ,  F01D5/14 ,  F02C3/04 ,  F02C7/18

    Abstract: A blade assembly includes a blade and a blade platform secured to the blade. The blade extends radially from the blade platform. The blade platform includes at least one platform airflow passage located therein. A gusset extends from the blade to the blade platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage. a gas turbine engine includes a combustor and a plurality of gas turbine engine components located in fluid communication with the combustor. The gas turbine engine component includes an airfoil portion and a platform secured to the airfoil portion. The platform includes at least one platform airflow passage positioned therein. A gusset extends from the airfoil portion to the platform. The gusset includes a gusset airflow passage fluidly connected to the platform airflow passage to convey an airflow to the platform airflow passage.

    Non-line of sight electro discharge machined part
    17.
    发明授权
    Non-line of sight electro discharge machined part 有权
    非线视觉放电加工零件

    公开(公告)号：US09561555B2

    公开(公告)日：2017-02-07

    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: B23H1/00 ,  F01D5/18 ,  B23H7/26 ,  B23H7/30 ,  B23H9/10

    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。

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