Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity
Numerical Study on the Solid Fuel Rocket Scramjet Combustor with Cavity
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固体燃料火箭超燃冲压发动机空腔燃烧室数值研究
DOI：
10.3390/en12071235
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发表时间：
2019-03
期刊：
影响因子：
3.2
通讯作者：
Chen Binbin
中科院分区：
文献类型：
--
作者：
Li Chaolong;Xia Zhixun;Ma Likun;Zhao Xiang;Chen Binbin
基于固体推进剂的超燃冲压发动机是未来高超声速飞行器动力装置的良好补充。提出了一种新的固体燃料超燃冲压发动机燃烧室结构，即固体燃料火箭超燃冲压发动机燃烧室。进行数值研究是为了模拟25公里高度上马赫数为6的飞行环境。采用三维雷诺平均Navier-Stokes方程和剪切应力输运（SST）k − ω湍流模型，分析了凹腔及其位置对燃烧室的影响。在数值计算方法验证的基础上，论证了带凹腔SFRSCRJ燃烧室的可行性。结果表明，后台阶超燃冲压发动机燃烧室结构能够抵抗超声速燃烧室燃烧产生的高压。SFRSCRJ燃烧室的总燃烧效率主要取决于富燃料气体中颗粒的燃烧。合理的燃烧组织可以促进颗粒燃烧，提高燃烧效率。在所考虑的四种构型中，中凹腔构型的燃烧效率最高，可达70%左右。因此，凹腔可以有效地提高SFRSCRJ燃烧室的燃烧效率。
Scramjet based on solid propellant is a good supplement for the power device of future hypersonic vehicles. A new scramjet combustor configuration using solid fuel, namely, the solid fuel rocket scramjet (SFRSCRJ) combustor is proposed. The numerical study was conducted to simulate a flight environment of Mach 6 at a 25 km altitude. Three-dimensional Reynolds-averaged Navier–Stokes equations coupled with shear stress transport (SST) k − ω turbulence model are used to analyze the effects of the cavity and its position on the combustor. The feasibility of the SFRSCRJ combustor with cavity is demonstrated based on the validation of the numerical method. Results show that the scramjet combustor configuration with a backward-facing step can resist high pressure generated by the combustion in the supersonic combustor. The total combustion efficiency of the SFRSCRJ combustor mainly depends on the combustion of particles in the fuel-rich gas. A proper combustion organization can promote particle combustion and improve the total combustion efficiency. Among the four configurations considered, the combustion efficiency of the mid-cavity configuration is the highest, up to about 70%. Therefore, the cavity can effectively increase the combustion efficiency of the SFRSCRJ combustor.
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