发明名称 |
Hybrid impingement cooled turbine nozzle |
摘要 |
A turbine nozzle for a gas turbine engine includes: (a) spaced-apart arcuate inner and outer bands (34, 32); (b) a hollow, airfoil-shaped turbine vane (30) extending between the inner and outer bands, the interior of the vane (30) defining at least a forward cavity (54) and a mid-cavity (56) positioned aft of the forward cavity (54); (c) a hollow impingement insert (60) received inside the mid-cavity (56), the impingement insert (60) having walls which are pierced with at least one impingement cooling hole; (d) a passage in the turbine vane (30) at a radially outer end of the forward cavity (54) adapted to be coupled to a source of cooling air; and (e) a passage in the inner band in fluid communication with a radially inner end of the forward cavity (54) and a radially inner end of the impingement insert (60). |
申请公布号 |
EP2105580(A1) |
申请公布日期 |
2009.09.30 |
申请号 |
EP20090155388 |
申请日期 |
2009.03.17 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
FLODMAN, DAVID ALLEN;SHAPIRO, JASON DAVID;MANNING, ROBERT FRANCIS;GLEDHILL, MARK DOUGLAS;HOOPER, TYLER FREDERICK |
分类号 |
F01D11/20;F01D11/22 |
主分类号 |
F01D11/20 |
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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