Experimental investigation of transient injection phenomena with flash evaporation in rocket combustors at vacuum conditions (B04)

当在真空条件下点燃低温上级火箭发动机或反应与控制系统发动机时，推进剂以过热状态被注入燃烧室。在这种情况下，推进剂会剧烈蒸发，这被称为闪蒸。在B4项目中，对控制液氧闪蒸的参数进行了详细的实验研究。这一结果可用于开发和验证用于描述使用低温燃料的火箭燃烧室的瞬时启动的模型。

When igniting cryogenic upper stage rocket engines or reaction and control system engines under vacuum conditions propellants are injected in a superheated state into the combustor. Under these conditions the propellants evaporate violently, which is referred to a flash evaporation. In the project B4 the parameters controlling the flash evaporation of liquid oxygen are analysed in a detailed experimental investigation. The results can be used to develop and verify models for the description of the transient start-up of rocket combustion chambers that are operated with cryogenic fuels.