| 发明名称 |
Gas turbine engine system |
| 摘要 |
A turbine blade for a gas turbine engine comprises an aerofoil having a suction and pressure side. The pressure side is provided with a reflex curvature at the aerofoil trailing edge region so as to reduce the thickness of the aerofoil in that region.
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| 申请公布号 |
US6544001(B2) |
申请公布日期 |
2003.04.08 |
| 申请号 |
US20010944366 |
申请日期 |
2001.09.04 |
| 申请人 |
ROLL-ROYCE PLC |
发明人 |
DAILEY GEOFFREY M |
| 分类号 |
B22C9/10;F01D5/18;(IPC1-7):F01D5/18 |
主分类号 |
B22C9/10 |
| 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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