发明名称 |
Transition channel of a gas turbine |
摘要 |
At least one guiding blade or guiding rib (31) is provided between two adjacent support ribs (27,28) that are spaced apart in the circumference direction of a transition channel. The outgoing edge (32) of the guiding rib extends upstream of the outgoing edges (33) of the support ribs. |
申请公布号 |
EP1621733(B1) |
申请公布日期 |
2017.03.01 |
申请号 |
EP20050015705 |
申请日期 |
2005.07.20 |
申请人 |
MTU Aero Engines AG |
发明人 |
Hoeger, Martin, dr.;Malzacher, Franz |
分类号 |
F01D9/02;F01D5/14;F01D9/04 |
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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