再生冷却技术是超燃冲压发动机燃烧室热防护的关键技术。
Regenerative cooling technology is one of the key technologies to thermally protect scramjet chamber.
对比再生冷却分析了不同注入率对壁面温度、冷却效率以及边界层厚度的影响；
The influences of porosity on the local blowing ratio, wall temperature and boundary layer thickness were compared with the effects with regenerative cooling.
为了能够快速而准确地得到再生冷却推力室的温度分布，建立了一种计算再生冷却推力室温度场的方法。
To quickly and accurately obtain temperature distribution in regeneratively-cooled thrust chamber, a method of computing temperature field in thrust chamber was developed.
然后使用这种方法研究了气壁材料、气壁厚度和冷却液流量对推力室再生冷却的影响，获得了比较满意的结果。
Then using this method, influence of gas wall material, gas wall thickness and flow rate of coolant on regenerative cooling of thrust chamber was investigated. The results were satisfactory.
本文的主要工作面向液体火箭发动机设计CAD技术，并选择再生冷却式液体火箭发动机推力室设计CAD技术研究作为方向。
This paper mainly focuses on CAD of LRE design, and present studies on CAD technique of recycled cooling LRE combustion chamber.
本文的主要工作面向液体火箭发动机设计CAD技术，并选择再生冷却式液体火箭发动机推力室设计CAD技术研究作为方向。
This paper mainly focuses on CAD of LRE design, and present studies on CAD technique of recycled cooling LRE combustion chamber.
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