发明授权
US06470671B1 Coolable nozzle and method for producing such a nozzle for a rocket engine
有权
可冷却喷嘴及其制造用于火箭发动机的喷嘴的方法
- 专利标题： Coolable nozzle and method for producing such a nozzle for a rocket engine
- 专利标题（中）： 可冷却喷嘴及其制造用于火箭发动机的喷嘴的方法
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申请号： US09539043申请日： 2000-03-30
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公开(公告)号： US06470671B1公开(公告)日： 2002-10-29
- 发明人: Joachim Kretschmer
- 申请人： Joachim Kretschmer
- 优先权： DE19915082 19990401
- 主分类号： F02K964
- IPC分类号： F02K964
摘要：
A regeneratively coolable nozzle for a rocket engine is formed by winding a tubular material (6) onto a winding mandrel to produce a helical composite structure (5), through which a coolant can flow during operation of the nozzle. The spiral composite structure (5) is fixed temporarily and the fixed composite structure (5) is removed from the winding mandrel. Then an inner heat resistant, load bearing layer (9) is applied to the radially inner hot-gas facing surface (H) of the fixed composite structure (5). The present nozzle is lightweight and withstand a high coolant pressure.
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