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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 new supersonic combustion flow field analysis model considering shock train structure is developed for the optimization design of the aspirated hypersonic vehicle. In this model, aerodynamic thermodynamic phenomena such as ignition and combustion in a combustion chamber are described by solving a rigid ordinary differential governing equations coupled with a finite rate chemical reaction. The Billig shock train model is used to simulate the combustion high pressure propagation process. The model was used to calculate the flow field of the three typical configurations of combustion chamber such as “straight section + expansion section”, “back stage” and “branch injection”. The results show that the model correctly reflects the physicochemical process in the supersonic combustor flow. Compared with the experimental data, the wall pressure distribution calculated by the model is better than the model without the shock wave structure.