发明名称 |
Cooling a turbine blade for gas turbine engine |
摘要 |
A turbine blade (30) includes a platform (40) and an airfoil (42) extending radially from the platform (40). An internal cooling circuit is formed in the airfoil (42) for circulating a coolant therethrough to cool the airfoil (42). At least one supply passage (110) is provided to direct some of the coolant that has passed at least partially through the internal cooling circuit onto the platform (40) for cooling the platform (40). <IMAGE> |
申请公布号 |
EP1205636(A3) |
申请公布日期 |
2003.10.29 |
申请号 |
EP20010309237 |
申请日期 |
2001.10.31 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
DEMERS, DANIEL EDWARD;MANNING, ROBERT FRANCIS;ACQUAVIVA, PAUL JOSEPH |
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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地址 |
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