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    TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN A GAS TURBINE ENGINE
    1.
    发明公开
    TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN A GAS TURBINE ENGINE 审中-公开
    涡轮机框架冷却系统和用于燃气涡轮发动机的组装方法

    公开(公告)号：EP3205830A1

    公开(公告)日：2017-08-16

    申请号：EP16202245.3

    申请日：2016-12-05

    申请人： General Electric Company

    发明人： LIPINSKI, Thomas ,  LACHAPELLE, Donald George ,  MOORE, Kenneth Jay ,  TRACEY, Bradford Alan ,  WAYMEYER, Stephen Joseph

    IPC分类号： F01D9/06 ,  F01D25/14 ,  F01D25/16 ,  F02C7/12

    CPC分类号： F01D25/14 ,  F01D9/065 ,  F01D11/005 ,  F01D17/085 ,  F01D17/105 ,  F01D17/145 ,  F01D25/12 ,  F01D25/145 ,  F01D25/162 ,  F01D25/24 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/20 ,  Y02T50/675

    摘要： A turbine frame cooling system (100) for use with a gas turbine engine (10) includes an outer ring (102) defining a cavity (118) and a hub (104) positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings (106) coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings (108) coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops (116) coupled to the outer ring. The plurality of air scoops extend into a bypass stream (40) and are configured to channel a bypass air cooling flow (52) into the cavity of the outer ring.

    摘要翻译： 用于燃气涡轮发动机（10）的涡轮机框架冷却系统（100）包括限定空腔（118）的外环（102）和位于外环径向内侧的毂（104）。 涡轮机框架冷却系统还包括联接在外环与轮毂之间的多个周向间隔开的第一整流罩（106）以及联接在外环与轮毂之间的多个周向间隔开的第二整流罩（108），其中第一整流罩 而第二整流罩交替地位于轮毂周围。 涡轮机框架冷却系统还包括联接到外环的多个周向间隔开的空气勺（116）。 多个空气汲取器延伸到旁路流（40）中并且被配置成将旁路空气冷却流（52）引导到外环的空腔中。