发明名称 |
GAS TURBINE ENGINE AIRFOIL WITH LEADING EDGE TRENCH AND IMPINGEMENT COOLING |
摘要 |
A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge. |
申请公布号 |
WO2015112225(A2) |
申请公布日期 |
2015.07.30 |
申请号 |
WO2014US64018 |
申请日期 |
2014.11.05 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SLAVENS, THOMAS N.;SNYDER, BROOKS E. |
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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