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为了研究固体火箭发动机尾焰注水流场对导流槽排导通畅性的影响,设计了火箭发动机和导流槽缩比模型并完成了发动机系留点火及注水试验。结果表明:向尾焰注水能够使流入导流槽内混合气体温度降低到原来的1/2,实现对导流槽的热防护;但大量的水蒸气生成并与燃气混合后进入导流槽,影响了导流槽的排导性能。为了解决该问题,建立了在Mixture多相流模型基础上的数值计算模型,在Mixture多相流模型中以源项形式添加液态水与燃气两相流作用过程中的质量和能量转移方程,通过与试验数据对比,验证计算模型具有较高的精度和可靠性,并进一步得出燃气流场和液体流场的相互作用和对导流槽的排导性能的影响。在此基础上分析了发动机喷管数量、导流型面曲线类型对导流槽排导通畅性的影响,为火箭发动机尾焰注水系统工程应用提供参考。
In order to study the effect of the wake injection flow field of the solid rocket motor on the conductance of the guide groove, the model of rocket engine and diversion groove reduction ratio was designed and the ignition and water injection test of the engine was completed. The results show that the water injection into the tail flame can reduce the temperature of the mixed gas flowing into the guide groove to 1/2 and realize the thermal protection of the guide groove; however, a large amount of water vapor is generated and mixed with the gas to enter the guide groove, Affect the guide channel guide performance. In order to solve this problem, a numerical model based on the Mixture multi-phase flow model is established. The mass and energy transfer equations of the two-phase flow of liquid water and gas are added as a source term in the Mixture multiphase flow model. Compared with the experimental data, the verification calculation model has high accuracy and reliability, and the interaction between the gas flow field and the liquid flow field and the influence on the conductance performance of the guide groove are further obtained. On this basis, the influence of the number of engine nozzles and the curve type of the guide surface on the conductance of the guide groove is analyzed, which provides a reference for the engineering application of the rocket engine tail water injection system.