发明名称 |
AIRFOIL WITH SKIN CORE COOLING |
摘要 |
A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall. |
申请公布号 |
EP3060760(A4) |
申请公布日期 |
2016.11.02 |
申请号 |
EP20140855974 |
申请日期 |
2014.10.16 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
HAGAN, BENJAMIN F.;WAITE, RYAN ALAN |
分类号 |
F01D5/18;F01D25/12;F02C7/18 |
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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