发明名称 |
CROSSOVER COOLED AIRFOIL TRAILING EDGE |
摘要 |
A turbine airfoil (12) includes pressure and suction sidewalls (20,22) having first and second flow channels (32,34) disposed therebetween and separated by a longitudinally extending bridge (36). The bridge includes a row of inlet holes (46), and a row of outlet holes (48) extends from the second channel toward the trailing edge (26) of the airfoil. A row of turbulator ribs (50) is disposed inside the second channel along the pressure sidewall and are longitudinally elongate and substantially colinear. The ribs face the inlet holes for crossover impingement cooling from the air channeled therefrom.
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申请公布号 |
CA2415542(A1) |
申请公布日期 |
2003.07.11 |
申请号 |
CA20032415542 |
申请日期 |
2003.01.02 |
申请人 |
GENERAL ELECTRIC COMPANY |
发明人 |
MANNING, ROBERT FRANCIS;TASLIM, MOHAMMAD ESMAIL |
分类号 |
F01D5/18;(IPC1-7):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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