| 发明名称 |
GAS TURBINE |
| 摘要 |
The pressure ratio .DELTA.P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely.
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| 申请公布号 |
CA2365090(A1) |
申请公布日期 |
2002.07.25 |
| 申请号 |
CA20012365090 |
申请日期 |
2001.12.14 |
| 申请人 |
MITSUBISHI HEAVY INDUSTRIES, LTD. |
发明人 |
UEMATSU, KAZUO;ITO, EISAKU |
| 分类号 |
F01D5/12;F01D5/14;F01D5/16;F01D9/02;F01D25/30;F02C7/00;(IPC1-7):F02C7/00 |
主分类号 |
F01D5/12 |
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代理人 |
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