侧向旋转射流进气对固冲发动机性能的影响

Influence of dual-side inlet swirl-injection on performance of solid rocket ramjet

采用Reynolds应力方程模型及涡耗散燃烧模型,在不同旋转工况下给定相同进气流量,对侧向进气固冲发动机补燃室湍流反应流场进行了数值计算,得到了燃烧产物的平衡组分、燃烧温度和其他热力学参数,并在此基础上计算了补燃室燃烧效率、发动机推力等参数。数值模拟表明,对于侧向进气固体火箭冲压发动机,在空气射流中引入旋转流动,能有效提高补燃室内的燃烧效率,进一步提高发动机性能。燃烧效率随旋流强度呈先增大、后又减小的规律。采用最佳旋流数的旋转进气后,可使发动机推力提高约2.3%。

Given the same inlet flow under the different swirl-mode working condition, the turbulent reaction flow field in the side inlet afterburning chamber of solid rocket ramjet was numerically simulated by means of Reynolds stress equation model and eddy-dissipation combustion model. Some thermodynamic parameters of combustion products including equilibrium ingredients and combustion temperature were obtained. On the basis of the above parameters, combustion efficiency and ramjet thrust in the afterburning chamber were also calculated. The numerical simulation results show that air inlet swirl injection can efficiently improve combustion efficiency in the chamber of side inlet solid rocket ramjet, so the performance of the ramjet can be further improved. Combustion efficiency follows the rule of first increase, and then decrease with the swirl injection intensity. The ramjet thrust can increase by about 2.3% by using optimal swirl number.