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    AIRFOIL
    11.
    发明公开
    AIRFOIL 审中-公开
    翼型

    公开(公告)号：EP3219919A1

    公开(公告)日：2017-09-20

    申请号：EP17160960.5

    申请日：2017-03-14

    Applicant: United Technologies Corporation

    Inventor： LEON, Jeffrey ,  NADEAU, Daniel C. ,  LEVINE, Jeffrey R. ,  KAUFMAN, Eleanor D. ,  ALLEN, Richard N. ,  MOLONY, Evan P. ,  ANSELMI, Gregory

    IPC: F01D5/18 ,  B22C9/10

    Abstract: An airfoil (200), comprising an airfoil body and an internal cavity (210) within the airfoil body. The internal cavity (210) may comprise an outer edge (212) comprising a first outer scallop (213) and a second outer scallop (213), an inner edge (211) opposite the outer edge (212), the inner edge (211) comprising a first inner scallop (213) and a second inner scallop (213), a leading edge (208) spanning between the outer edge (212) and the inner edge (211), and a trailing edge (209) spanning between the outer edge (212) and the inner edge (211) and opposite the leading edge (208). Between the outer edge (212), the inner edge (211), the leading edge (208), and the trailing edge (209), the internal cavity may comprise eight columns of pedestals (221...228) disposed axially relative to one another and axially between the leading edge (208) and the trailing edge (209).

    Abstract translation: 一种翼型（200），包括翼型主体和翼型主体内的内腔（210）。 内腔210可以包括外边缘212，该外边缘212包括第一外扇贝213和第二外扇贝213，与外边缘212相对的内边缘211， ）包括第一内扇贝（213）和第二内扇贝（213），跨越外边缘（212）和内边缘（211）之间的前缘（208），以及跨越 外边缘（212）和内边缘（211）并与前缘（208）相对。 在外边缘（212），内边缘（211），前缘（208）和后缘（209）之间，内腔可以包括相对于轴向设置的八列基座（221 ... 228） 彼此并且在前缘（208）和后缘（209）之间轴向地延伸。

    AIRFOIL PLATFORM WITH COOLING FEED ORIFICES
    12.
    发明公开
    AIRFOIL PLATFORM WITH COOLING FEED ORIFICES 审中-公开
    麻辣M EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN EN

    公开(公告)号：EP3045666A1

    公开(公告)日：2016-07-20

    申请号：EP16151762.8

    申请日：2016-01-18

    Applicant: United Technologies Corporation

    Inventor： BOEKE, Mark A. ,  ANDERSON, Kristopher K. ,  DEGRAY, Jeffrey J. ,  LEVINE, Jeffrey R. ,  RILEY, Sarah ,  SALZILLO, Jr., Richard M.

    IPC: F01D9/04 ,  F01D25/12

    CPC classification number: F01D25/12 ,  F01D9/023 ,  F01D9/04 ,  F01D9/06 ,  F05D2240/81 ,  Y02T50/676

    Abstract: An airfoil platform includes a platform body (100) having an arcuate base (108) defining a centerline axis (A). A rail (110) extends radially outboard from a side of the arcuate base. A feed orifice (114) is defined at least partially in the rail. The inner diameter edge (122) of an axially facing opening (124) of the feed orifice is spaced apart radially outboard of an outer diameter surface of the arcuate base. A method for manufacturing an airfoil platform includes providing an airfoil platform body (100) and forming the feed orifice (114) through the rail. Forming the feed orifice through the rail includes forming the feed orifice radially outboard of and spaced apart from the outer diameter surface of the arcuate base.

    Abstract translation: 翼型平台包括具有限定中心线轴线（A）的弓形基座（108）的平台体（100）。 轨道（110）从弓形底座的一侧沿径向外侧延伸。 进料口（114）至少部分地限定在轨道中。 进料孔的轴向面向的开口（124）的内径边缘（122）在弧形基部的外径表面的径向外侧间隔开。 一种用于制造翼型平台的方法包括提供翼型平台本体（100）并且通过导轨形成进料孔（114）。 通过导轨形成进料口包括沿着弧形底座的外径表面径向外侧和间隔开地形成进料孔。

    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE
    16.
    发明公开
    IMPROVED COOLING FOR A TURBINE AIRFOIL TRAILING EDGE 审中-公开
    改进的冷却涡轮叶片后缘

    公开(公告)号：EP2877705A2

    公开(公告)日：2015-06-03

    申请号：EP13813721.1

    申请日：2013-03-28

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： LEVINE, Jeffrey R. ,  MONGILLO, Dominic J. ,  DONNELL, Brandon S.

    IPC: F01D5/18 ,  F02C7/12

    Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.

    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE
    20.
    发明公开
    GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE 审中-公开
    燃气涡轮发动机SERPENTINE COOLING PASSAGE

    公开(公告)号：EP2895694A1

    公开(公告)日：2015-07-22

    申请号：EP13836460.9

    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，所述冷却通道提供通过内壁彼此分开并通过弯曲流体连接的上游部分和下游部分。 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。 湍流促进剂从靠近下游部分弯曲处的外壁延伸。 邻近邻近下游部分弯曲处的内壁的停滞区中不存在湍流促进剂

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