为了研究射流预冷技术对预压段温度场的影响,采用欧拉-拉格朗日方法建立了液滴雾化蒸发过程的三维数学模型.气液两相之间的传质和动量交换是通过双向耦合的方法实现的.通过与已有试验结果的比较,验证了该数学模型的准确性.采用响应面法分析了水气比、喷射速度、液滴尺寸和喷嘴锥角对航空发动机进气温度的影响,建立了四因素三水平响应面法.结果表明:发动机进气空气温度的降温比为3.67％～26.02％.建立了基于多元回归方法的可视化非线性多变量设计优化方程,得到了水气比、喷射速度、液滴尺寸和喷嘴锥角对进气冷却效果的影响.当水气比为0.08、液滴尺寸为10.47 µm、喷射速度为39.52m/s、喷嘴锥角为24.79°时,发动机最低预压缩冷却段温度为449.60 K.
Response surface characteristic analysis of jet precooling on aero-engine inlet temperature
To investigate the influence of jet precooling technology on the temperature field in the pre-compressor section,a three-dimensional mathematical model was proposed to study the droplet atomization and evaporation process using the Eulerian-Lagrangian method.The mass transfer and momentum exchange between gas-liquid phase were realized by two-way coupling method.Compared with existing experimental results,the accuracy of the temperature in the mathematical model was verified.The effects of water-air ratio,velocity,particle size,and cone angle on the temperature of inlet air were analyzed by response surface methodology in the aero-engine,and a four-factor and three-level response surface methodology was established.The results showed that the temperature drop ratio of engine intake air temperature was 3.67％-26.02％.The visualized nonlinear multivariable design optimization equation based on multiple regression method and the effects of water-air ratio,velocity,particle size and cone angle on inlet cooling effect were obtained.When the water-air ratio was 0.08,the particle size was 10.47μm,the velocity was 39.52 m/s and the cone angle was 24.79°,the minimum inlet temperature of aero-engine was 449.60 K.
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