| 发明名称 |
Guide for air flow between compressor and combustion chamber of aircraft turbine engine has independent rectifier supported by diffuser |
| 摘要 |
<p>The air flow guide between a turbine compressor and combustion chamber (14) consists of a rectifier (10) and a diffuser (12) in the form of separate components, assembled with the rectifier supported by the diffuser and fastened with a fixing on the diffuser's inlet end. The rectifier is made up of two cylindrical rings (58, 60) that fit onto the inlet end of the diffuser, with the inner ring fastened to it by a nut and bolt fixing.</p> |
| 申请公布号 |
FR2887924(A1) |
申请公布日期 |
2007.01.05 |
| 申请号 |
FR20050006678 |
申请日期 |
2005.06.30 |
| 申请人 |
SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION SNECMA SOCIETE ANONYME |
发明人 |
DAGUENET LUC;PIEUSSERGUES CHRISTOPHE;SABLAYROLLES PIERRE;TOUCHAUD STEPHANE |
| 分类号 |
F02C7/00;F04D29/54 |
主分类号 |
F02C7/00 |
| 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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