射流预冷对航空发动机进气温度的特征性分析  

Response surface characteristic analysis of jet precooling on aero-engine inlet temperature

作　　者：冯爽 李宝宽[1] 杨晓晰 谢业平 张海洋 FENG Shuang;LI Baokuan;YANG Xiaoxi;XIE Yeping;ZHANG Haiyang(Department of Thermal Engineering,Northeastern University,Shenyang 110819,China;Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China;Liaoning Key Laboratory of Aeroengine Impact Dynamics,Shenyang Engine Research Institute,Aero Engine Corporation of China,Shenyang 110015,China)

机构地区：[1]东北大学热能工程系,沈阳110819 [2]中国航发沈阳发动机研究所,沈阳110015 [3]中国航发沈阳发动机研究所辽宁省航空发动机冲击动力学重点实验室,沈阳110015

出　　处：《航空动力学报》2024年第7期177-188,共12页Journal of Aerospace Power

基　　金：中央高校基本科研业务费专项基金(N2025013)。

摘　　要：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.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.

关 键 词：射流预冷 响应面分析 进气温度 雾化 蒸发 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]