Abstract: The Vortex Combustion Cold Wall is an innovation cooling method for liquid rocket engine combustion chamber,which has the advantages of simple structure,low-cost and high reliability. Based on the introduction the principle of Vortex-cooled Combustion Chamber (VCCC),the vortex flow configuration was analyzed and the distributional characteristics of bidirectional vortex was demonstrated. By means of the cold flow simulation,preliminary analysis of vortex flow configuration was performed. Velocity and energy decreased in the flow field due to viscous can affect the efficiency of propellant mixing and combustion under reactive flow conditions. Optimizing the incidence angle of oxidizer nozzles shows that the oxidizer nozzle with certain slope angle can enhance the velocity and vorticity of inner vortex regions and improve the combustion efficiency of propellants in VCCC.

Key words: Vortex-cooled;Thrust chamber;Analysis of vortex configuration;Incidence angle of oxidizer nozzle

摘要： 涡流冷却是一种新型液体火箭发动机推力室冷却方法,可以简化推力室结构,降低成本,提高可靠性。本文首先介绍该类型推力室的工作原理,并对涡流的结构进行了理论分析,得出内外涡流的速度分布特点。通过冷流场计算,验证了涡流结构分析的正确性。由于流体的粘性,减小了内部涡流的速度及涡量强度,影响推进剂的掺混及燃烧。通过对氧化剂喷嘴入射角的优化,发现氧化剂喷嘴倾斜一定的角度,可以增加内部涡流的速度及涡量强度,将有助于提高涡流冷却推力室中推进剂的燃烧效率。

关键词: 涡流冷却;推力室;涡流结构分析;氧化剂喷嘴入射角