发明名称 |
Airfoil cooling with staggered refractory metal core microcircuits |
摘要 |
A turbine engine component has an airfoil portion with a pressure side wall and a suction side wall and a cooling system. The cooling system has at least one cooling circuit disposed longitudinally along the airfoil portion. Each cooling circuit has a plurality of staggered internal pedestals for increasing heat pick-up.
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申请公布号 |
US2008145235(A1) |
申请公布日期 |
2008.06.19 |
申请号 |
US20060641628 |
申请日期 |
2006.12.18 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
CUNHA FRANCISCO J.;PIETRASZKIEWICZ EDWARD F. |
分类号 |
F01D5/18;B22D23/00;B23P15/00 |
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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