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    MANUFACTURING METHOD FOR A DUAL WALL COMPONENT
    22.
    发明公开
    MANUFACTURING METHOD FOR A DUAL WALL COMPONENT 审中-公开
    HERSTELLUNGSVERFAHRENFÜREIN DOPPELWANDBAUTEIL

    公开(公告)号：EP3042040A4

    公开(公告)日：2017-05-31

    申请号：EP14841618

    申请日：2014-09-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W

    IPC: F01D5/14 ,  F01D5/18 ,  F01D25/12 ,  F02C7/18 ,  F04D29/38 ,  F04D29/58

    CPC classification number: F01D5/147 ,  F01D5/18 ,  F01D5/187 ,  F01D9/041 ,  F01D11/08 ,  F05D2220/32 ,  F05D2230/30 ,  F05D2260/204 ,  F05D2260/22141 ,  F05D2300/606

    Abstract: A dual wall component includes a first outer wall extending from a leading edge to a trailing edge, a first inner wall spaced from the first outer wall by a plurality of first cavities and first ribs, a second inner wall spaced from the first inner wall by a plurality of second cavities and second ribs, and a second outer wall extending from the leading edge to the trailing edge and spaced from the second inner wall by a plurality of third cavities and third ribs. Portions of the first and second outer walls have thicknesses less than about 0.018″ (0.457 mm). In a method for forming a dual wall component, component walls are formed by additive manufacturing and without using cores to form the cavities.

    Abstract translation: 双壁部件包括从前缘延伸到后缘的第一外壁，通过多个第一腔和第一肋与第一外壁间隔开的第一内壁，与第一内壁隔开一定距离的第二内壁， 多个第二腔和第二肋以及从所述前缘延伸到所述后缘并通过多个第三腔和第三肋与所述第二内壁间隔开的第二外壁。 第一和第二外壁的部分具有小于约0.018“（0.457mm）的厚度。 在用于形成双壁构件的方法中，构件壁通过增材制造形成，并且不使用芯来形成空腔。

    SURFACE STRUCTURES WITH A COOLING HOLE PATTERN AND CORRESPONDING METHOD OF FORMING
    23.
    发明公开
    SURFACE STRUCTURES WITH A COOLING HOLE PATTERN AND CORRESPONDING METHOD OF FORMING 审中-公开
    美国麻醉科学研究所麻省理工学院

    公开(公告)号：EP3163021A1

    公开(公告)日：2017-05-03

    申请号：EP16185760

    申请日：2016-08-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  CAVALLO GINA

    IPC: F01D5/18 ,  F01D9/06 ,  F23R3/00

    CPC classification number: F04D29/582 ,  F01D5/186 ,  F01D9/065 ,  F02C7/18 ,  F04D29/164 ,  F04D29/526 ,  F04D29/542 ,  F04D29/644 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2240/11 ,  F05D2240/35 ,  F05D2240/81 ,  F05D2260/202 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/03042 ,  Y02T50/672 ,  Y02T50/676

    Abstract: A surface structure having a filmhole pattern is disclosed. The filmhole pattern may be an offset herringbone pattern (52). For instance, the surface structure may have rows of filmholes arranged in filmrows (55), each filmrow (55) divided into groups of filmholes. A first group may be oriented to direct cooling air generally outward over a surface of the surface structure and a second group may be oriented to direct cooling air generally inward over a surface of the surface structure. Between the first group and the second group of filmholes in each filmrow (55), a transition region exists. The adjacent filmrows (55) are arranged to enhance the effectiveness of the convective cooling proximate to the transition regions by causing each filmrow (55) to direct cooling air over the transition region of an adjacent filmrow (55).

    Abstract translation: 公开了一种具有膜孔图案的表面结构。 薄膜图案可以是偏移人字形图案（52）。 例如，表面结构可以具有布置在薄膜（55）中的一排薄膜孔，每个薄膜（55）分成薄膜组。 第一组可以被定向成将冷却空气大致向外引导到表面结构的表面上，并且第二组可以被定向成将冷却空气大致向内引导到表面结构的表面上。 在每个成像线（55）中的第一组和第二组膜之间存在过渡区。 相邻的薄膜（55）被布置成通过使每个薄膜（55）将冷却空气引导到相邻的薄膜（55）的过渡区域上，来增强靠近过渡区域的对流冷却的有效性。

    SUPPLY DUCT FOR COOLING AIR
    28.
    发明公开
    SUPPLY DUCT FOR COOLING AIR 审中-公开
    用于冷却空气的进料通道

    公开(公告)号：EP3022421A4

    公开(公告)日：2016-08-03

    申请号：EP14826896

    申请日：2014-07-02

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  TRINDADE RICARDO

    IPC: F02C7/12 ,  F01D25/12 ,  F02C6/08

    CPC classification number: F02C7/18 ,  F01D5/085 ,  F01D9/06 ,  F01D9/065 ,  F01D25/08 ,  F01D25/14 ,  F02C3/04 ,  F02C6/08 ,  F05D2220/32 ,  F05D2260/205 ,  F05D2260/232 ,  F05D2270/3062 ,  Y02T50/676

    Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.

    Abstract translation: 在特征实施例中，燃气涡轮发动机具有压缩机部分，其具有下游转子和在压缩机部分下游的扩散器。 燃烧器在扩散器的下游接收空气。 涡轮部分具有至少一个待冷却的部件。 导管与扩散器间隔开并限定冷却气流路径。 冷却气流路径与扩散器下游的气流分离，并且通过燃烧器。 导管将冷却空气传递到要冷却的部件。

    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION
    29.
    发明公开
    TRAILING EDGE OR TIP FLAG ANTIFLOW SEPARATION 审中-公开
    HINTERKANTEN- ODER SPITZENFLAGGEN-FLUSSTRENNUNG

    公开(公告)号：EP2828485A4

    公开(公告)日：2016-07-27

    申请号：EP13763814

    申请日：2013-01-10

    Applicant: UNITED TECHNOLOGIES CORP ,  GAUTSCHI STEVEN BRUCE ,  SPANGLER BRANDON W ,  QUACH SAN ,  MONGILLO DOMINIC J JR

    Inventor： GAUTSCHI STEVEN BRUCE ,  SPANGLER BRANDON W ,  QUACH SAN ,  MONGILLO DOMINIC J JR

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F05D2240/122 ,  F05D2240/125 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2250/314 ,  F05D2250/324 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: An airfoil includes a leading edge, a trailing edge region, a suction surface, a pressure surface, a cooling passageway, and a column of flow separators. The suction surface and the pressure surface both extend axially between the leading edge and the trailing edge region, as well as radially from a root section of the airfoil to a tip section of the airfoil to define a central cavity of the airfoil. The cooling passageway is located within the central cavity at the trailing edge region. The column of flow separators is located in the cooling passageway adjacent the trailing edge and includes a first flow separator having a first longitudinal axis and a second flow separator having a second longitudinal axis. The first longitudinal axis is offset at an angle with respect to the first longitudinal axis.

    Abstract translation: 翼型件包括前缘，后缘区域，吸力表面，压力表面，冷却通道和流动分离器柱。 吸力表面和压力表面两者都在前缘和后缘区域之间轴向延伸，并且从翼型的根部径向延伸到翼型的尖端部分，以限定翼型的中心空腔。 冷却通道位于后缘区域的中心腔内。 流动分离器的柱位于与后缘相邻的冷却通道中，并且包括具有第一纵向轴线的第一流动分离器和具有第二纵向轴线的第二流动分离器。 第一纵向轴线相对于第一纵向轴线以一定角度偏移。

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