发明名称 |
GAS TURBINE ENGINE INCLUDING AIRFOILS HAVING AN IMPROVED AIRFOIL FILM COOLING CONFIGURATION AND METHOD THEREFOR |
摘要 |
<p>An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling hole at a location on the airfoil outer surface relative to the first and second datum structures. As a result, each film cooling hole has a centerline extending therethrough that forms a compound angle with respect to a tangent to the outer surface, and the distance between the centerlines of each film cooling hole is at least a predetermined minimum distance.</p> |
申请公布号 |
EP1709299(A1) |
申请公布日期 |
2006.10.11 |
申请号 |
EP20050712534 |
申请日期 |
2005.01.27 |
申请人 |
HONEYWELL INTERNATIONAL INC. |
发明人 |
BORNS, FREDRICK, G.;MCDONALD, ROBERT;RIAHI, ARDESHIR |
分类号 |
F01D5/18 |
主分类号 |
F01D5/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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