发明名称 |
GAS TURBINE ENGINE COOLING HOLE WITH CIRCULAR EXIT GEOMETRY |
摘要 |
A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface. |
申请公布号 |
US2014090384(A1) |
申请公布日期 |
2014.04.03 |
申请号 |
US201213629705 |
申请日期 |
2012.09.28 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
MCBRIEN JOHN;SPANGLER BRANDON W.;DEVORE MATTHEW A. |
分类号 |
F01D5/18;F01D9/02;F23R3/02 |
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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