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发明公开
EP2103799A3 Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine 有权
Raketenschubdüseund Steuerungsverfahren derAbgasströmung在einem Raketentriebwerk

Rocket nozzle and control method for combustion of the exhaust gas flow in rocket engine
摘要：
A rocket nozzle (8) includes a dual-bell nozzle (10) and a gas introducing section (40A, 40B, 40C, 40D) configured to introduce gas into space (80) surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle (20) bell-shaped and surrounding an upstream portion (81) of the space, and a second stage nozzle (30) bell-shaped and surrounding a downstream portion (82) of the space. The dual-bell nozzle has an inflection point (12) between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet (45, 63) provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.
摘要（中）：

火箭喷嘴（8）包括双钟形喷嘴（10）和被配置为将气体引入由双钟形喷嘴包围的空间（80）中的气体引入部分（40A，40B，40C，40D）。 燃烧气体在空间流动。 双钟形喷嘴包括钟形的第一级喷嘴（20）并且围绕该空间的上游部分（81），并且第二级喷嘴（30）是钟形的并围绕该空间的下游部分（82） 。 双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点（12）。 气体导入部包括设置在第一级喷嘴的内壁面的气体入口（45,63）。 气体从气体入口引入空间。

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