发明名称 |
COOLED STATIONARY BLADE FOR A GAS TURBINE |
摘要 |
In the present invention, seal air passes through a tube extending in a stationary blade from an outside shroud to an inside shroud, flows into a cavity to keep the pressure in the cavity high so as to seal the high-temperature combustion gas, and is discharged to a passage. Part of cooling air flows into an air passage to cool the leading edge portion, passes through the peripheral portion of the inside shroud to cool the same, and is discharged to a passage. The remaining cooling air flows into a passage, passes through a serpentine cooling flow path consisting of air passages having turbulators, and is discharged through air cooling holes formed at the trailing edge. The cooling air passing through the passage at the leading edge portion cools the peripheral portion of the inside shroud as well as the leading edge portion of blade, by which the cooling efficiency is increased.
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申请公布号 |
CA2231690(C) |
申请公布日期 |
2001.08.14 |
申请号 |
CA19982231690 |
申请日期 |
1998.03.10 |
申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
TOMITA, YASUOKI;SUENAGA, KIYOSHI;FUKUNO, HIROKI |
分类号 |
F01D9/02;F01D5/18;F01D9/04;F02C7/18;F02D9/02;(IPC1-7):F01D5/18;F01D25/12 |
主分类号 |
F01D9/02 |
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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