| 发明名称 |
Cooling system for a gas turbine blade and corresponding gas turbine blade |
| 摘要 |
A cooling system for an airfoil portion (112) of a turbine engine component is provided. The cooling system includes a first cavity (142) dedicated to cooling a trailing edge portion (118) of an airfoil portion (112) and a second cavity (146) dedicated to cooling an aft portion (144) of a pressure side wall (114).
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| 申请公布号 |
EP1953343(A2) |
申请公布日期 |
2008.08.06 |
| 申请号 |
EP20080250187 |
申请日期 |
2008.01.15 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
SPANGLER, BRANDON W.;PIETRASZKIEWICZ, EDWARD F. |
| 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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