关键词: 超声速燃烧室;主动冷却;传热分析;超临界态;煤油替代模型

Abstract: A method of one-dimensional heat transfer analysis,dealing with the coupling effect of the combustion flow,coolant flow and combustor wall,has been developed for the study of an regenerative fuel cooling system for Mach 2.5 supersonic combustor.The analysis includes the air dissociation effect at high temperature,combustion characteristics of kerosene and thermophysical properties of the supercritical kerosene.Based on the measured static pressure along the combustor wall and heat transfer characteristics of supercritical kerosene,the analysis is applied to investigate the cooling process and cooling effect at different combustion and cooling conditions.The analysis shows that the wall heat flux with combustion can exceed 1 MW/m2,which is 2~3 times the value of that without combustion.Under cooling conditions with a relatively low coolant flow rate,high temperature regions and large temperature variations exist on the hot-side combustor wall.With increase in the coolant flow rate,the cooling effect is improved significantly and the fuel exit temperature decreases.

Key words: Supersonic combustor;Active cooling;Heat transfer analysis;Supercritical state;Kerosene surrogate