发明公开
EP3205830A1 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
- 专利标题： TURBINE FRAME COOLING SYSTEMS AND METHODS OF ASSEMBLY FOR USE IN A GAS TURBINE ENGINE
- 专利标题（中）： 涡轮机框架冷却系统和用于燃气涡轮发动机的组装方法
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申请号： EP16202245.3申请日： 2016-12-05
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公开(公告)号： EP3205830A1公开(公告)日： 2017-08-16
- 发明人: LIPINSKI, Thomas , LACHAPELLE, Donald George , MOORE, Kenneth Jay , TRACEY, Bradford Alan , WAYMEYER, Stephen Joseph
- 申请人： General Electric Company
- 申请人地址： 1 River Road Schenectady, NY 12345 US
- 专利权人： General Electric Company
- 当前专利权人： General Electric Company
- 当前专利权人地址： 1 River Road Schenectady, NY 12345 US
- 代理机构： Williams, Andrew Richard
- 优先权： US201615041524 20160211
- 主分类号： F01D9/06
- IPC分类号： F01D9/06 ; F01D25/14 ; F01D25/16 ; F02C7/12
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.
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