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Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
Gas turbine engine including airfoils having an improved airfoil film cooling configuration and method therefor
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机译:包括具有改进的翼型膜冷却构造的翼型的燃气涡轮发动机及其方法
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摘要
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.
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