发明名称 |
Blade cooling air supplying system of gas turbine |
摘要 |
In the present disclosure, an air pipe extends through a stationary blade between outer and inner shrouds. Further, an air passage is directed to a lower portion of the stationary blade and is communicated with the air pipe so that a serpentine cooling passage is formed. The air enters a cavity from the air passage and is discharged to a gas passage through an air hole, a passage and a seal. Thus, the cavity is sealed at a high pressure. Cooling air is supplied from the air passage to a rotating blade through a cooling air hole, a cooling air chamber, a radial hole and a lower portion of a platform. The stationary blade is cooled by the air through the air passage. The cooling air can be supplied to the rotating blade at a low temperature and a high pressure as they are. Accordingly, the air can be also supplied to the rotating blade when a rotor is cooled by vapor.
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申请公布号 |
US6077034(A) |
申请公布日期 |
2000.06.20 |
申请号 |
US19980038451 |
申请日期 |
1998.03.11 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
TOMITA, YASUOKI;FUKUNO, HIROKI;HASHIMOTO, YUKIHIRO;SUENAGA, KIYOSHI |
分类号 |
F01D5/08;F01D5/18;F01D9/02;F01D9/04;F01D9/06;F01D11/04;F02C7/18;(IPC1-7):F01D5/18 |
主分类号 |
F01D5/08 |
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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