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    SUPPLY DUCT FOR COOLING AIR
    1.
    发明申请
    SUPPLY DUCT FOR COOLING AIR 审中-公开
    供应冷却空气

    公开(公告)号：WO2015009449A1

    公开(公告)日：2015-01-22

    申请号：PCT/US2014/045175

    申请日：2014-07-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： SPANGLER, Brandon W. ,  TRINDADE, Ricardo

    IPC: F02C7/12 ,  F01D25/12

    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，该压缩机部分具有在压缩机部分下游的下游转子和扩散器。 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。

    AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES
    3.
    发明申请
    AIRFOIL DESIGN HAVING LOCALIZED SUCTION SIDE CURVATURES 审中-公开
    AIRFOIL设计具有本地化吸收侧曲线

    公开(公告)号：WO2014022762A1

    公开(公告)日：2014-02-06

    申请号：PCT/US2013/053399

    申请日：2013-08-02

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： AGGARWALA, Andrew S. ,  ALLEN-BRADLEY, Eunice ,  GROVER, Eric A. ,  TRINDADE, Ricardo

    IPC: F02C7/00 ,  F01D5/00

    CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D5/148 ,  F01D5/186 ,  F05D2240/124 ,  F05D2250/713

    Abstract: An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.

    Abstract translation: 用于燃气涡轮发动机的翼型件包括具有横截面的径向延伸体。 横截面包括前缘，后缘，压力侧和吸力侧。 压力侧以主要凹陷的曲率在前缘和后缘之间延伸。 吸入侧以主要凸起的曲率在前缘和后缘之间延伸。 吸入侧包括侧面为前后凸部的大致平坦部。 在另一个实施例中，吸力侧包括一系列局部曲率变化，其产生与后缘间隔开的吸入侧的凸曲率中的拐点。

    TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES
    4.
    发明申请
    TURBINE BLADE PLATFORM WITH U-CHANNEL COOLING HOLES 审中-公开
    涡轮叶片平台与U型通道冷却孔

    公开(公告)号：WO2014003958A1

    公开(公告)日：2014-01-03

    申请号：PCT/US2013/043340

    申请日：2013-05-30

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： ZELESKY, Mark, F. ,  TRINDADE, Ricardo ,  TELLER, Bret, M. ,  LEWIS, Scott, D. ,  BEATTIE, Jeffrey, S. ,  JACQUES, Jeffrey, Michael ,  RAPP, Brandon, M.

    IPC: F02C7/12 ,  F01D5/18 ,  F02K3/00

    CPC classification number: F01D5/085 ,  F01D5/081 ,  F01D5/18 ,  F05D2240/81 ,  Y02T50/676

    Abstract: A turbine blade for a gas turbine engine includes an airfoil including leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface extending in a radial direction. The trailing edge is arranged on an aft side of the turbine blade. A root supports a platform from which the airfoil extends and a cooling passage extends within the root in the radial direction to the airfoil. A lower wing is arranged beneath the platform on the aft side and extends in an axial direction to provide a U-shaped channel with the platform that extends in a circumferential direction. An impingement hole extends from the U-channel to the cooling passage.

    Abstract translation: 一种用于燃气涡轮发动机的涡轮叶片包括一个翼型件，其包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸的外部翼面。 后缘布置在涡轮叶片的后侧。 根部支撑翼型件延伸的平台，并且冷却通道在根部内沿径向方向延伸到翼型件。 下翼设置在平台的后侧，在轴向方向上延伸，以提供具有沿圆周方向延伸的平台的U形通道。 冲击孔从U形通道延伸到冷却通道。

    AIRFOIL WITH ARCED PEDESTAL ROW
    7.
    发明公开
    AIRFOIL WITH ARCED PEDESTAL ROW 审中-公开

    公开(公告)号：EP3650650A1

    公开(公告)日：2020-05-13

    申请号：EP19208383.0

    申请日：2019-11-11

    Applicant: United Technologies Corporation

    Inventor： ARISI, Allan N. ,  TRINDADE, Ricardo ,  MONGILLO, Dominic J. ,  PROPHETER-HINCKLEY, Tracy A.

    IPC: F01D5/18

    Abstract: An airfoil (60) includes an airfoil section (66; 166) that has an airfoil wall (68) that defines a leading end (68a), an arced trailing end (68b), and first and second sides (68c, 68d) that join the leading end (68a) and the arced trailing end (68b). The first and second sides (68c, 68d) span in a longitudinal direction (Al) between first and second ends (68e, 68f). The airfoil wall (68) circumscribes an internal core cavity (70) that includes an exit region (74, 174) that spans between the first and second ends (68e, 68f) and that opens through the arced trailing end (68b). The exit region (74; 174) includes pedestals (76) arranged in a plurality of longitudinal pedestal rows (78, 178). At least one of the longitudinal pedestal rows (78; 178) is straight and at least one of the longitudinal pedestal rows (78; 178) is arced.

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