发明申请
US20130209232A1 MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS
审中-公开
具有热障涂层的气体涡轮发动机组件中的多孔冷却孔
- 专利标题： MULTI-LOBED COOLING HOLES IN GAS TURBINE ENGINE COMPONENTS HAVING THERMAL BARRIER COATINGS
- 专利标题（中）： 具有热障涂层的气体涡轮发动机组件中的多孔冷却孔
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申请号： US13543932申请日： 2012-07-09
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公开(公告)号： US20130209232A1公开(公告)日： 2013-08-15
- 发明人: JinQuan Xu , Edward F. Pietraszkiewicz , Mark F. Zelesky , Glenn Levasseur , Dominic J. Mongillo
- 申请人： JinQuan Xu , Edward F. Pietraszkiewicz , Mark F. Zelesky , Glenn Levasseur , Dominic J. Mongillo
- 主分类号： F01D5/18
- IPC分类号： F01D5/18 ; F01D9/02 ; B05D3/06 ; B05D7/00 ; B05D3/14
摘要：
A gas turbine engine component includes a wall with an inner face and an outer skin. A plurality of cooling air holes extend from the inner face to the outer skin. The cooling holes include an inlet merging into a metering section, and a diffusion section downstream of the metering section, and extend to an outlet at the outer skin. The diffusion section includes a plurality of lobes. A coating layer is formed on the outer skin, with at least a portion of the plurality of lobes formed within the thermal barrier coating. A method of forming such a component is also disclosed.
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