固体火箭发动机尾焰注水流场对导流槽排导性能影响研究

Effect of Rocket Engine Jet Flow with Water Injection on Air-flow Exhaust of Gas-flow-guided Channel

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。

To study the influence of rocket engine jet flow with water injection on the gas-flow exhaust of gas-flow-guided channel, the scaled models of rocket engine and gas-flow-guided channel are designed, by which the mooring ignition and water injection are tested. The results show that the temperature of mixed gas in the gas-flow-guided channel could be decreased to half of the original temperature. The cooling effect is obvious. However, a large amount of water vapor is generated and enters into the gas- flow-guided channel after mixing with combustion gas, thus influencing the exhaust of combustible air- flow. A numerical model based on the Mixture muhiphase flow model is established. The interphase heat and mass transfer equations are added into the unsteady gas-liquid two-phase flow field model . The com- parison of calculated data with experimental data shows that the proposed model has higher calculation ac- curacy and reliability, and the interaction of gas and liquid flow fields and its influence on the patency of gas-flow-guided channel are clearly shown. For further study, the influences of the number of nozzles and the type of surface curve are analyzed.