再生冷却燃气对流换热系数计算方法优化研究  

Optimization for calculation method of gas convective heat transfer coefficient inside regeneratively-cooled chamber

作　　者：吴有亮 张成印[1] 潘浩[1] 李强[1] 程圣清 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2018年第1期22-26,共5页Journal of Rocket Propulsion

摘　　要：目前通常使用Bartz方法来计算液体火箭发动机推力室燃气强迫对流传热系数。Bartz方法没有考虑推力室燃烧区域分布和边界层厚度变化等实际情况对燃气热流的影响,不能很好的反映燃烧区域的燃气热流密度分布,其计算结果与试验存在一定的偏差。在Bartz方法的基础上,考虑燃烧区域长度、边界层厚度变化和流动加速性的影响,建立了修正的Bartz方法,再分别采用Bartz方法、修正的Bartz方法和Pavli方法,进行了推力室再生冷却传热计算。与液氧/甲烷发动机推力室试验结果对比表明,在三种方法中,修正的Bartz方法计算结果与试验结果最为接近。最后,采用修正的Bartz方法研究了推力室压力和混合比对再生冷却的影响。The gas convective heat transfer coefficient inside the liquid rocket engine combustion chamber is usually evaluated by using the Bartz equation. As the Bartz equation does not take account the influence of combustion zone distribution in the thrust chamber, thickness variation of the boundary layer and other actual situations on fuel gas heat flux, it can not well present the gas heat flux density distribu- tion inside combustion chamber, especially in the combustion zone near the injector. It is not fit well with the results of the experiments. In this paper, a modified Bartz equation is introduced. This modified Bartz equation take account the effects of combustion zone distribution, thickness variation of the boundary lay- er and flow acceleration in nozzle. The modified method of Bartz equation is determined. Pavli equation was used to evaluate the gas heat transfer coefficient. The comparison results show that the result calculat- ed by the modified Bartz equation is fit well with the result of LOX/methane thrust chamber experiment. The modified Bartz equation was used to analyze the effect of the chamber pressure and mixture ratio on regeneratively-eooled chamber performance.

关 键 词：液氧/甲烷发动机 再生冷却 传热 巴兹法 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]