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    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS
    21.
    发明申请
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE WITH CHEVRONS 有权
    燃气涡轮发动机SERPENTINE冷却通风与CHEVRONS

    公开(公告)号：US20140212297A1

    公开(公告)日：2014-07-31

    申请号：US13728069

    申请日：2012-12-27

    Applicant: United Technologies Corporation

    Inventor： Travis Goeller ,  Erik R. Granstrand ,  Irwin D. Singer ,  Dominic J. Mongillo, JR. ,  Edward F. Pietraszkiewicz

    IPC: F01D5/18

    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。

    COOLING HOLE WITH CRENELLATION FEATURES
    22.
    发明申请
    COOLING HOLE WITH CRENELLATION FEATURES 有权
    冷凝孔与发条特点

    公开(公告)号：US20140193246A1

    公开(公告)日：2014-07-10

    申请号：US14204465

    申请日：2014-03-11

    Applicant: United Technologies Corporation

    Inventor： Glenn Levasseur ,  Edward F. Pietraszkiewicz

    IPC: 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。

    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINING SYSTEM
    23.
    发明申请
    NON-LINE OF SIGHT ELECTRO DISCHARGE MACHINING SYSTEM 审中-公开
    非线性电子放电加工系统

    公开(公告)号：US20140183164A1

    公开(公告)日：2014-07-03

    申请号：US13729328

    申请日：2012-12-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

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

    IPC: B23H1/04

    CPC classification number: B23H1/04 ,  B23H7/26 ,  B23H9/10 ,  B23H9/14

    Abstract: An electro discharge machining system includes a guide having first and second portions that are non-colinear with respect to one another. A consumable electrode is housed within the guide and configured to drill cooling holes in a component. A controller is programmed to position the guide and electrode to a desired position with respect to the component. An electro discharge machining guide includes first and second portions that are non-colinear with respect to one another and that include a passage configured to receive an electrode.

    Abstract translation: 放电加工系统包括具有相对于彼此不共线的第一和第二部分的引导件。 消耗性电极容纳在引导件内并构造成钻出部件中的冷却孔。 编程控制器以将引导件和电极相对于部件定位到期望的位置。 电放电加工引导件包括相对于彼此非共线的第一和第二部分，并且包括构造成接收电极的通道。

    Preferential flow distribution for gas turbine engine component
    24.
    发明授权
    Preferential flow distribution for gas turbine engine component 有权

    公开(公告)号：US11125434B2

    公开(公告)日：2021-09-21

    申请号：US16214824

    申请日：2018-12-10

    Applicant: United Technologies Corporation

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

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

    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.

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