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湍流涡结构的作用导致以扩散形式喷射燃料的超声速燃烧过程通常以部分预混的方式进行,为了使火焰面模型对这一燃烧过程描述的更准确,在模型中对扩散燃烧和预混燃烧状态均需要予以合理考虑。基于低Ma条件多区域火焰面模型(MRF)思想,发展得到了适用于超声速条件的部分预混火焰面模型。以碳氢燃料超声速双燃烧室结构作为验证算例,采用k-ωSST湍流模型、部分预混火焰面模型和乙烯(C2H4)的28组分72步化学反应机理对超声速湍流燃烧流场进行了数值研究。计算结果与实验数据吻合良好,验证了模型的准确性。加权系数计算结果表明,在中心剪切层和下壁面附近区域流场主要由预混燃烧控制,而其他大部分区域则由扩散燃烧控制。
The effect of turbulent vortex structure is that the supersonic combustion process that injects fuel in a diffused manner is usually performed in a partially premixed manner. In order to make the flame surface model more accurately described for this combustion process, the diffusion combustion and the premixed combustion state All need to be given due consideration. Based on the idea of low Ma multi-region flame surface model (MRF), a partially pre-mixed flame surface model suitable for supersonic conditions was developed. Taking the supersonic dual-combustor structure of hydrocarbon-fuel as an example, the flow field of supersonic turbulent combustion was numerically calculated by k-ωSST turbulence model, partial premixed flame model and ethylene / C2H4 / the study. The calculated results are in good agreement with the experimental data, which verifies the accuracy of the model. The calculation of the weighted coefficients shows that the flow field in the area near the center shear layer and the lower wall is mainly controlled by premixed combustion, while most of the other areas are controlled by diffusion combustion.