发明名称 |
GAS TURBINE ENGINE HIGH LIFT AIRFOIL COOLING IN STAGNATION ZONE |
摘要 |
An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. A stagnation line is located on the pressure side wall aft of the leading edge. A cooling passage is provided between the pressure and suction side walls. Forward-facing cooling holes are provided adjacent to the stagnation line on the pressure side wall and oriented toward the leading edge. |
申请公布号 |
EP2964932(A1) |
申请公布日期 |
2016.01.13 |
申请号 |
EP20140760123 |
申请日期 |
2014.02.26 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
QUACH, SAN;DEVORE, MATTHEW, A. |
分类号 |
F02C7/18;F01D5/18 |
主分类号 |
F02C7/18 |
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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