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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。

    5.
    发明专利
    未知

    公开(公告)号：AT424963T

    公开(公告)日：2009-03-15

    申请号：AT05253843

    申请日：2005-06-21

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HUDSON ERIC A ,  HARDING BENJAMIN R

    IPC: B23P15/04 ,  F01D5/18

    Abstract: A cooled turbine engine component is made by providing first and second pieces (46,44) respectively having first and second surfaces (64,68). At least one circuit (100) is formed in at least one of the first and second surfaces (68). A first plurality of apertures (114) is provided in the first piece (46) to form inlets to the at least one circuit (100). A second plurality of apertures (140) is provided in the second piece (44) to form outlets to the at least one circuit (100). A combination of the first and second pieces is assembled and integrated.

    7.
    发明专利
    未知

    公开(公告)号：DE602005019002D1

    公开(公告)日：2010-03-11

    申请号：DE602005019002

    申请日：2005-06-10

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： HARDING BENJAMIN R ,  HUDSON ERIC A

    IPC: F01D5/18

    Abstract: A vane assembly (10) suitable for a turbine engine features a refractory vane (12) with an internal cavity (20) and a pair of flexible metallic baffles (26) extending into the cavity (20) from spanwisely opposite ends of the vane (12). A rigid fastener (40), such as a nut and bolt assembly applies a tensile load to the baffles (26). The tensile load is reacted out as a compressive load applied to the vane (12). In another embodiment, the baffle (26) is relatively rigid but the fastener (52) is flexible. The compressive loading exerted on the vane (12) counteracts the brittleness customarily exhibited by refractory materials and imparts damage tolerance to the vane (12). The arrangement also allows the use of a metal baffle (26) that can be easily secured to the vane (12) and dispenses with any need for a potentially troublesome seal between the baffles and the spanwise extremities of the vane (12).

    Turbine airfoil platform cooling circuit
    9.
    发明专利
    Turbine airfoil platform cooling circuit 未知

    公开(公告)号：SG127789A1

    公开(公告)日：2006-12-29

    申请号：SG200601656

    申请日：2006-03-14

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CUNHA FRANK J ,  COUCH ERIC ,  SANTELER KEITH A ,  GAYMAN SCOTT W ,  HUDSON ERIC A ,  JOE CHRISTOPHER ,  LETIZIA ERIC

    Abstract: An airfoil assembly includes an airfoil extending away from a platform. One or more cooling circuits are formed through the platform in order to provide cooling of the platform. The cooling circuit may include a downwardly directed inlet receiving cooling air from below the platform. The cooling air is then directed in a direction generally parallel to the outer surface of the platform and through exits formed through the outer surface of the platform. The cooling circuit may optionally include a plurality of pedestals extending from an outer wall to an inner wall of the cooling circuit to increase the rigidity and the cooling function of the cooling circuit.

    AIRFOIL COOLING CIRCUITS
    10.
    发明公开
    AIRFOIL COOLING CIRCUITS 审中-公开
    冷却回路翼

    公开(公告)号：EP2867476A4

    公开(公告)日：2015-08-12

    申请号：EP13822892

    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.

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