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    AIRFOIL COOLING CIRCUITS
    2.
    发明申请
    AIRFOIL COOLING CIRCUITS 审中-公开
    空气冷却电路

    公开(公告)号：WO2014018138A2

    公开(公告)日：2014-01-30

    申请号：PCT/US2013037302

    申请日：2013-04-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUDSON ERIC A ,  PROPHETER-HINCKLEY TRACY A ,  QUACH SAN ,  DEVORE MATTHEW A

    IPC: F01D5/18 ,  F01D5/14 ,  F02C7/00

    CPC classification number: F01D5/187 ,  B22C9/10 ,  B22C9/108 ,  B22C9/24 ,  F01D5/186 ,  F05D2230/211 ,  F05D2260/204 ,  F05D2260/2212

    Abstract: An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.

    Abstract translation: 机翼包括前缘和后缘; 第一和第二侧从前缘延伸到后缘，每个侧面具有外表面; 位于第一和第二侧之间以及前缘和后缘之间的芯通道; 以及位于所述芯通道和所述第一侧的外表面之间的壁结构。 所述壁结构包括与所述芯通道连通的多个冷却流体入口，用于从所述芯通道接收冷却流体;在所述第一侧的外表面上的多个冷却流体出口，用于排出冷却流体，并沿着所述外部形成冷却膜 第一侧的表面，以及与多个冷却流体入口和多个冷却流体出口连通的多个冷却通道。 一个冷却通道的至少一部分在相邻的冷却流体出口之间延伸。

    AIRFOIL HAVING INTERNAL LATTICE NETWORK
    6.
    发明申请
    AIRFOIL HAVING INTERNAL LATTICE NETWORK 审中-公开
    具有内部网格网络的AIRFOIL

    公开(公告)号：WO2014011290A3

    公开(公告)日：2014-04-03

    申请号：PCT/US2013036511

    申请日：2013-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  TRACY ANITA L ,  LOUREIRO SERGIO M ,  KLUCHA AGNES

    IPC: F01D5/14 ,  F02C7/00

    CPC classification number: F04D29/388 ,  F01D5/16 ,  F02C3/04 ,  F02K3/06 ,  F04D29/325 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/30

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A lattice network connects the first side and the second side. The lattice network includes at least one enlarged node spaced apart from the first side wall and the second side wall and ribs that extend from the at least one enlarged node. Each of the ribs connects to one of the first side wall and the second side wall.

    Abstract translation: 翼型包括限定纵向轴线的翼型体。 翼型体包括前缘和后缘以及第一侧壁和与第一侧壁间隔开的第二侧壁。 第一侧壁和第二侧壁连接前缘和后缘并且至少部分地限定翼型体中的空腔。 格子网络连接第一面和第二面。 格子网络包括与第一侧壁和第二侧壁间隔开的至少一个放大节点以及从至少一个放大节点延伸的肋。 每个肋连接到第一侧壁和第二侧壁中的一个。

    TURBINE ENGINE VARIABLE AREA VANE
    8.
    发明申请
    TURBINE ENGINE VARIABLE AREA VANE 审中-公开
    涡轮发动机可变区域VANE

    公开(公告)号：WO2014011304A3

    公开(公告)日：2014-04-10

    申请号：PCT/US2013037618

    申请日：2013-04-22

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： SPANGLER BRANDON W ,  PROPHETER-HINCKLEY TRACY A

    IPC: F02C9/20 ,  F01D17/16 ,  F02K3/00

    CPC classification number: F01D17/162 ,  F05D2260/202

    Abstract: A turbine engine stator vane is provided that rotates about an axis, and includes an airfoil, a flange and a shaft. The airfoil extends axially between a first airfoil end and a second airfoil end. The airfoil includes a concave side surface, a convex side surface and a cavity. The concave and the convex side surfaces extend between an airfoil leading edge and an airfoil trailing edge. The cavity extends axially into the airfoil from a cavity inlet in an end surface at the second airfoil end. The flange is connected to the second airfoil end. The flange extends circumferentially around at least a portion of the cavity inlet, and radially away from the concave and the convex side surfaces to a distal flange edge. The shaft extends along the axis, and is connected to the second airfoil end.

    Abstract translation: 提供涡轮发动机定子叶片，其绕轴线旋转，并且包括翼型件，法兰和轴。 机翼在第一翼型端和第二翼型端之间轴向延伸。 翼型件包括凹面侧面，凸面侧面和空腔。 凹面和凸面侧面在翼型前缘和翼型后缘之间延伸。 空腔从第二翼型端的端面中的腔入口轴向延伸到翼型中。 法兰连接到第二翼型端。 凸缘围绕空腔入口的至少一部分周向延伸，并且从凹入和凸出的侧表面径向地远离到远侧凸缘边缘。 轴沿轴线延伸，并连接到第二翼型端。

    AIRFOIL HAVING MINIMUM DISTANCE RIBS
    9.
    发明申请
    AIRFOIL HAVING MINIMUM DISTANCE RIBS 审中-公开
    AIRFOIL具有最小距离的RIBS

    公开(公告)号：WO2014011289A3

    公开(公告)日：2014-03-27

    申请号：PCT/US2013036510

    申请日：2013-04-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： FISK BENJAMIN T ,  PROPHETER-HINCKLEY TRACY A ,  DOLANSKY GREGORY M ,  TRACY ANITA L ,  TAFFET STEVEN

    IPC: F01D5/14 ,  F02C7/00

    CPC classification number: F01D5/147 ,  B23P15/02 ,  F01D5/187 ,  F05D2260/22141 ,  Y10T29/49336

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.

    Abstract translation: 翼型包括限定纵向轴线的翼型体。 翼型体包括前缘和后缘以及第一侧壁和第二侧壁，第二侧壁与第一侧壁间隔开以在其间限定弧线。 第一侧壁和第二侧壁连接前缘和后缘并且至少部分地限定翼型体中的空腔。 多个肋在腔内纵向延伸并且相对于纵向轴线彼此侧向间隔开。 在垂直于纵向轴线的至少一个平面中，每个肋沿着垂直于弧线的相应最小距离方向连接第一侧壁和第二侧壁。 各个最小距离方向中的至少两个是不平行的。

    AIRFOIL INCLUDING DAMPER MEMBER
    10.
    发明专利
    AIRFOIL INCLUDING DAMPER MEMBER 未知

    公开(公告)号：SG11201406220RA

    公开(公告)日：2014-11-27

    申请号：SG11201406220R

    申请日：2013-04-20

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： DOLANSKY GREGORY M ,  PROPHETER-HINCKLEY TRACY A ,  FISK BENJAMIN T

    IPC: F01D5/12 ,  F01D5/18 ,  F01D9/00 ,  F02K3/00 ,  F03C7/00

    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is faced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.

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