发明名称 |
Ejection nozzle for turbojet with integrated thrust reverser |
摘要 |
<p>The propulsion nozzle has an ejection channel (7) in an outer housing (9) with hot (14) and cold (16) shutters and a thrust reversal system (30) with two identical flaps (31, 32) that pivot at the rear end of the ejection channel on either side of its axis of symmetry (12). The nozzle incorporates a system for moving the flaps apart during take-off, in the form of a power cylinder (50) between supporting arms (33, 34), and the cold shutters are designed to ensure an obstacle-free aerodynamic profile with the flaps in take-off and cruising configurations.</p> |
申请公布号 |
EP1020631(B1) |
申请公布日期 |
2004.11.24 |
申请号 |
EP20000400066 |
申请日期 |
2000.01.13 |
申请人 |
SNECMA MOTEURS |
发明人 |
CHARIER, GILLES ALAIN;GUYONNET, XAVIER JEAN-MICHEL ANDRE;ROLLIN, GILLES LOUIS |
分类号 |
B64C15/00;F02K1/11;F02K1/60;F02K1/62;(IPC1-7):F02K1/11 |
主分类号 |
B64C15/00 |
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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