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    COMPONENTE DE TURBINA CON ENFRIAMIENTO DE PEDESTAL DE BANDERA DE PUNTA.
    1.
    发明专利
    COMPONENTE DE TURBINA CON ENFRIAMIENTO DE PEDESTAL DE BANDERA DE PUNTA. 未知

    公开(公告)号：MX2007013107A

    公开(公告)日：2009-02-13

    申请号：MX2007013107

    申请日：2007-10-19

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHEROLIS ANTHONY P ,  CHRISTOPHEL JESSE R ,  ABDEL-MESSEH WILLIAM

    IPC: F01D5/08 ,  F01D25/12 ,  F02C7/00

    Abstract: Se proporciona una paleta de turbina para un motor de turbina de gas con enfriamiento mejorado en una porción radialmente externa del borde de salida. Se proporciona una ruta de bandera de punta con un primer arreglo de pedestal para incrementar la transferencia de calor en el área. Además, un segundo arreglo de pedestal reemplaza los agujeros de dosificación que han sido colocados radialmente hacia adentro de la tira de punta. Los dos arreglos de pedestal proporcionan transferencia de calor mejorada en un área que ha sido sometida a la quema y estalación en la técnica previa.

    TURBINE COMPONENT WITH TIP FLAGGED PEDESTAL COOLING
    2.
    发明专利
    TURBINE COMPONENT WITH TIP FLAGGED PEDESTAL COOLING 未知

    公开(公告)号：SG142227A1

    公开(公告)日：2008-05-28

    申请号：SG2007088206

    申请日：2007-09-25

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CHEROLIS ANTHONY P ,  CHRISTOPHEL JESSE R ,  ABDEL-MESSEH WILLIAM

    Abstract: TURBINE COMPONENT WITH TIP FLAGGED PEDESTAL COOLING A turbine blade for a gas turbine engine is provided with improved cooling at a radially outer portion of the trailing edge. A tip flag path is provided with a first pedestal array to increase the heat transfer at the area. In addition, a second pedestal array replaces the metering holes which has been positioned radially inwardly of the tip strip. The two pedestal arrays provide improved heat transfer at an area which has been subject to burning and spallation in the prior art.

    ROTOR BLADE WITH L-SHAPED FEATHER SEAL
    3.
    发明公开
    ROTOR BLADE WITH L-SHAPED FEATHER SEAL 审中-公开
    ROTORBLATT MIT L-FÖRMIGERFEDERDICHTUNG

    公开(公告)号：EP2978938A4

    公开(公告)日：2016-07-20

    申请号：EP14775995

    申请日：2014-03-24

    Applicant: UNITED TECHNOLOGIES CORP

    Inventor： CORCORAN CHRISTOPHER ,  CHEROLIS ANTHONY P

    IPC: F01D11/00 ,  F01D5/14 ,  F01D11/22 ,  F02C7/28

    CPC classification number: F01D11/008 ,  F01D5/02 ,  F01D5/147 ,  F01D11/006 ,  F01D15/12 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2240/55 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/97

    Abstract: A turbine engine assembly arranged relative to an axis includes a rotor blade and a feather seal with an L-shaped geometry. The rotor blade includes an airfoil and a base. The airfoil extends axially between an upstream leading edge and a downstream trailing edge, and radially out from the base. The base includes a neck and a pocket. The neck extends axially to a downstream surface. The pocket extends laterally into the neck. The feather seal extends laterally into the pocket, and includes a down stream leg that extends substantially along the downstream surface.

    Abstract translation: 相对于轴线布置的涡轮发动机组件包括转子叶片和具有L形几何形状的羽毛密封。 转子叶片包括翼型件和底座。 翼型件在上游前缘和下游后缘之间轴向延伸，并从底座径向延伸。 底座包括一个脖子和一个口袋。 颈部轴向延伸到下游表面。 口袋横向延伸到颈部。 羽毛密封件横向延伸到袋中，并且包括基本上沿着下游表面延伸的下游腿。

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