发明名称 |
Aircraft bypass gas turbine engine trailing edge geometry alters trailing edge gas either side of a base angle |
摘要 |
<p>An aircraft gas turbine has a low-pressure stage with a rotating blade disc in front of a disc set of fixed vanes. Each blade has a leading edge and a trailing edge. The flow deflection angle at the trailing edge periodically increases and decreases with respect to a base angle.</p> |
申请公布号 |
DE102005021058(A1) |
申请公布日期 |
2006.11.09 |
申请号 |
DE20051021058 |
申请日期 |
2005.05.06 |
申请人 |
MTU AERO ENGINES GMBH |
发明人 |
METSCHER, MARTIN |
分类号 |
F01D5/14;F01D9/04;F15D1/10 |
主分类号 |
F01D5/14 |
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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