RBCC发动机亚燃模态热环境分析

针对RBCC（火箭基组合循环）发动机的亚燃模态，通过三维数值模拟计算分析了不同的工况下RBCC发动机中的受热情况，得到热载荷分布。其中一次火箭、小支板尾端、凹腔出口受热最为严重。计算发现一次火箭的流量越大，对流换热系数越大。支板壁喷会产生二氧化碳剪切层，影响燃烧效率，但是会降低热流密度。通过较为系统的热力分析，为RBCC发动机热防护提供一定的设计依据。

Research of Thermal Environment on Ramjet Mode of RBCC

Heat transfer of RBCC (Rocket Based Combined Cycle) engine under different working conditions was investigated through 3-D numerical simulation and analysis, meanwhile, distribution of heat flux was obtained. The thermal environment of primary rocket, the tail-edge of strut and the exit of cavity is rigorous. The results demonstrated that the heat transfer coefficient enhanced with increase of mass flow rate of primary rocket. During the working process, shear layer of CO2 was induced by injection of fuel from the strut wall, which weakened the heat flux, however, reduced the combustion efficiency. The results of forecast thermal environment can provide a reference to thermal structure design.