利索-全球专利检索

  1. 登录
  2. 注册
发明公开
CN101539074A 火箭喷嘴和用于火箭发动机内的燃烧气体流的控制方法 失效 - 权利终止

火箭喷嘴和用于火箭发动机内的燃烧气体流的控制方法
摘要：
本发明涉及一种火箭喷嘴和用于火箭发动机内的燃烧气体流的控制方法。所述火箭喷嘴(8)，包括双钟形喷嘴(10)和构造为将气体引入由该双钟形喷嘴围绕的空间(80)内的气体引入部(40A、40B、40C、40D)。燃烧气体在该空间中流动。该双钟形喷嘴包括第一级喷嘴(20)和第二级喷嘴(30)，该第一级喷嘴是钟形的并且围绕该空间的上游部(81)，该第二级喷嘴是钟形的并且围绕该空间的下游部(82)。双钟形喷嘴具有位于第一级喷嘴和第二级喷嘴之间的拐点(12)。该气体引入部包括设置到第一级喷嘴的内壁面上的气体入口(45、63)。将气体从该气体入口引入该空间中。
摘要（英）：

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.

公开/授权文献
0/0