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采用标准k-ω湍流模型和有限速率化学反应燃烧模型对二维轴对称雷诺平均N-S方程进行了数值计算,分析了超声速自由来流下冷流和H2-O210组分28步基元燃烧反应的底部排气近尾迹区流场特性,得到了不同排气参数下底部压力和回流区特性,与实验值相吻合。计算结果表明,在较小排气参数下添能比加质更有利于底压提高;随着排气总温的增加,最佳排气参数逐渐减小,回流区逐渐减小;回流区前滞止点位置随着排气参数、排气总温等因素变化而变化,而后滞止点位置几乎不变,但燃烧对回流区前后滞止点均产生了影响。
The two-dimensional Axisymmetric Reynolds-averaged Navier-Stokes equations were numerically calculated using a standard k-ω turbulence model and a limited-rate chemical reaction combustion model. The bottom of the 28-step elementary combustion reaction of supersonic free-flowing cold flow and H2-O210 The characteristics of the flow field near the wake region of the exhaust gas, the bottom pressure and the characteristics of the recirculation zone under different exhaust parameters are obtained, which are in good agreement with the experimental values. The calculated results show that under the condition of smaller exhaust gas parameters, the increase of bottom pressure can be more beneficial than the addition of mass; with the increase of the total exhaust gas temperature, the optimum exhaust gas parameters gradually decrease and the recirculation zone decreases gradually. The location of stagnation point changes with the change of exhaust parameters and the total exhaust temperature, but the location of after-stagnation point is almost unchanged. However, the combustion has an impact on the stagnation point before and after the recirculation zone.