发明名称 |
MICROCIRCUIT COOLING FOR VANES |
摘要 |
A turbine engine component (12) has an airfoil portion (10) with a suction side (14). The component (12) includes a cooling microcircuit (32) embedded within a wall structure forming the suction side (14). The cooling microcircuit (32) has at least one cooling film hole (36) positioned ahead of a gage point (38) for creating a flow of cooling fluid over an exterior surface of the suction side (14) which travels past the gage point (38). The cooling microcircuit is formed using refractory metal core technology. A method for forming the cooling microcircuit is described. |
申请公布号 |
KR20070054562(A) |
申请公布日期 |
2007.05.29 |
申请号 |
KR20060102330 |
申请日期 |
2006.10.20 |
申请人 |
UNITED TECHNOLOGIES CORP. |
发明人 |
CUNHA FRANCISCO J.;DAHMER MATTHEW T. |
分类号 |
F01D5/18;F01D5/00 |
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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