再生冷却氢氧推力室传热计算方法研究与优化

Research and Optimization of Heat Transfer Calculation Method for Regeneratively-cooled Hydrogen-oxygen Thrust Chamber

推力室传热计算对液体火箭发动机的研制非常关键,然而传统的再生冷却传热计算模型在针对氢氧火箭发动机时存在较大的误差。通过对推力室燃烧与流动过程的分析,并结合部件传热试验数据,考虑到雾化蒸发过程、燃气雷诺数大小以及普朗特数拟合公式计算偏差等因素的影响,提出改进的再生冷却传热计算模型。分别使用这两种模型对某型氢氧发动机推力室在不同工况下的传热过程开展计算,并与试车试验结果进行对比,发现改进的再生冷却传热模型具有更高的计算准确度和更好的针对不同工况的适用性。

The heat transfer calculation of the thrust chamber is very important for the development of the liquid rocket engine.However,the traditional regeneratively-cooled heat transfer calculation model has a large error in the hydrogen-oxygen rocket engine,which is not conducive to guiding engineering practice.Through the analysis of the combustion and flow process of the thrust chamber,combined with the heat transfer test data of the components,considering the influence of atomization and evaporation,the size of the gas reynolds number,and the deviation of the prandtl fitting formula,the improved regeneration cooling heat transfer calculation model.The two models are used to calculate the heat transfer process of a certain type of hydrogen-oxygen rocket engine thrust chamber under different working conditions,and the calculated results are compared with the test results.It is found that the improved regeneratively-cooled heat transfer model is more accurate,and has better applicability to different working conditions.