发明名称 |
Gas turbine rotor blade |
摘要 |
Provided is a gas turbine rotor blade comprising a plurality of first cooling holes for flow of a cooling gas bored in a blade portion along its lengthwise direction and a plurality of second cooling holes for flow of the cooling gas bored in a shroud along its plane direction so as to communicate with the first cooling holes, and being constructed such that the cooling gas can be flown in a uniform distribution. The plurality of the first cooling holes 3 for flow of the cooling gas are bored in the blade portion 2 and the plurality of the second cooling holes 5 for flow of the cooling gas are bored in the shroud 1 along its plane direction. The second cooling holes 5 communicate with the first cooling holes 3, hole to hole, via two-step holes 4, and the second cooling holes 5 are bored alternately on the dorsal side and the ventral side of the rotor blade. <IMAGE> |
申请公布号 |
EP0930418(B1) |
申请公布日期 |
2003.02.26 |
申请号 |
EP19980121905 |
申请日期 |
1998.11.18 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
FUKUE, ICHIRO;AKITA, EIJI;SUENAGA, KIYOSHI;TOMITA, YASUOKI |
分类号 |
F01D5/18;F01D5/20;F02C7/18 |
主分类号 |
F01D5/18 |
代理机构 |
|
代理人 |
|
主权项 |
|
地址 |
|