摘要
发展了一种考虑激波串结构的超声速燃烧流场分析模型,以应用于吸气式高超声速飞行器的设计优化过程。模型通过求解耦合有限速率化学反应的刚性常微分控制方程组来描述燃烧室内点火、燃烧等气动热力现象,采用Billig激波串模型模拟燃烧高压前传过程。采用该模型对"等直段+扩张段"、"后向台阶"和"支板喷射"三种典型构型燃烧室流场进行了计算。结果表明:所建模型正确地反映了超声速燃烧室流动中的物理化学过程;与实验数据比较,模型计算出的壁面压力分布比没有考虑激波串结构的模型符合的更好。
A supersonic combustion flow analysis model with shock train structure has been developed to support airbreathing hypersonic vehicle design optimization studies. The model solves a stiff set of ordinary differential equations coupled with the equations for finite-rate chemistry to describe the aerothermodynamics of ignition and combustion process within the supersonic combustor. The Billig＇s shock train model is used to simulate upstream propagation of high pressure within the combustor. The calculation of H2/air supersonic combustion flowfield in three typical combustors with ＂a constant-area section ＋ an expansion section＂, ＂backward-facing step＂, ＂strut injection＂ is used to validate the supersonic combustion model. The results show that the model presented explains accurately physical chemistry phenomena in supersonic combustion flowfield. Comparison with experimental data shows that the pressure distribution calculated by new model is closer to the experimental result than the previous model without shock train structure.
出处
《空气动力学学报》
EI
CSCD
北大核心
2012年第2期169-175,共7页
Acta Aerodynamica Sinica
基金
国家自然科学基金(90716013
10702029)
