发明名称 |
Turbomachine e.g. turbojet, for use in aircraft, has air guide including downstream end located at right side of dilution openings of inner wall of annular combustion chamber and at axial distance from air injecting unit |
摘要 |
<p>The turbomachine has a centrifugal compressor connected to an annular diffuser (312) to feed fuel to an annular combustion chamber (314). An annular inner casing (328) extends axially from the diffuser to an air injecting unit (346). An annular part (300) of an air guide made of sheet metal is driven by the inner casing, and extends around the inner casing to delimit with an inner wall of the chamber. The air guide includes a downstream end located at a right side of dilution openings (302, 304) of the inner wall of the chamber and at axial distance from the injecting unit.</p> |
申请公布号 |
FR2970512(A1) |
申请公布日期 |
2012.07.20 |
申请号 |
FR20110050327 |
申请日期 |
2011.01.14 |
申请人 |
SNECMA |
发明人 |
BOURGOIS SEBASTIEN, ALAIN, CHRISTOPHE;BENDERRADJI KAMEL |
分类号 |
F02C7/00;F23R3/50 |
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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