再生冷却，推进剂先流过推力室内外壁间的冷却套，带走燃气传给室壁的热量，然后进入喷注器喷入燃烧室的外冷却。
Concerning the physical process of the combustion and the heat transfer in the thrust chamber of the tripropellant liquid rocket engine, a numerical simulation method is developed about the interior combustion and the exterior regenerative cooling.
本文针对三组元液体火箭发动机推力室燃烧与传热的物理过程,对推力室内燃烧及外部再生冷却进行了仿真研究。
参考来源 - 三组元液体火箭发动机推力室燃烧与再生冷却仿真研究The failure of regenerative cooling due to propellant coking in a liquid rocket engine was investigated by numerically analyzing the flow and heat transfer in a mini cooling channel with artificial roughness.
针对液体火箭发动机再生冷却中的结焦问题,对含粗糙元微小冷却通道内的流动和换热进行数值研究。
参考来源 - 含人为粗糙元微小冷却通道内的流动与换热·2,447,543篇论文数据，部分数据来源于NoteExpress
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.
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