公开(公告)号：US20090235639A1

公开(公告)日：2009-09-24

申请号：US12200265

申请日：2008-08-28

申请人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

发明人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

IPC分类号： F02K9/08

CPC分类号： F02K1/38 ,  F02K9/48 ,  F02K9/58 ,  F02K9/82 ,  F02K9/972 ,  F05D2250/713

摘要： A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

摘要翻译： 火箭喷嘴包括双钟形喷嘴和构造成将气体引入由双钟形喷嘴包围的空间中的气体导入部。 燃烧气体在空间中流动。 双钟形喷嘴包括钟形状的第一级喷嘴并且围绕该空间的上游部分，以及第二级喷嘴钟形并围绕该空间的下游部分。 双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点。 气体导入部包括设置在第一级喷嘴的内壁面的气体入口。 气体从气体入口引入空间。