基于高空台排气扩压器非平衡流动k-ωSST湍流模型系数优化  

Optimizing k-ωSST Turbulence Model Coefficients for Non-equilibrium Flow in High Altitude Platform Exhaust Diffuser

作　　者：聂博文 张健平[1] 张松 但志宏 陈律江 杨豪 NIE Bowen;ZHANG Jianping;ZHANG Song;DAN Zhihong;CHEN Lvjiang;YANG Hao(Key Laboratory of Testing Technology for Manufacturing Process,Ministry of Education,Southwest University of Science and Technology,Mianyang Sichuan 621010,China;Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Mianyang Sichuan 621703,China)

机构地区：[1]西南科技大学制造过程测试技术教育部重点实验室,四川绵阳621010 [2]中国航空发动机集团有限公司四川燃气涡轮研究院,四川绵阳621703

出　　处：《机床与液压》2025年第2期125-133,共9页Machine Tool & Hydraulics

基　　金：中国航发四川燃气涡轮研究院外委课题(21zg8112);航空发动机高空模拟技术重点实验室稳定支持项目(20zh0149)。

摘　　要：为了准确模拟高空台排气扩压器湍流非平衡流动,采用Fluent软件分析k-ωSST湍流模型系数对扩压器出口静压模拟精度的影响,并通过响应面试验优化模型系数。结果表明:随着α_(1)的增大,模拟精度先提高后降低,达到0.341后保持不变。β^(*)的增大使模拟值逐渐接近目标值,从而提高精度;当模拟值大于目标值时,精度先降低再提高;而模拟值小于目标值时,精度急剧降低。β_(2)的增大也使得模拟值逐渐接近目标值,从而提高精度;当模拟值小于目标值,精度急剧降低。而σ_(ω2)的增大则使得模拟值迅速接近目标值,提高精度;但当模拟值小于目标值时,精度缓慢降低。模型系数α_(1)、β^(*),β_(2)、σ_(ω2)优选范围为0.2973~0.325、0.056~0.098、0.0756~0.089、0.69~1.1984。在此基础上,通过响应面试验显著性分析得到敏感性顺序为α_(1)>β_(2)>β^(*)>σ_(ω2),β^(*)与α_(1)、α_(1)和σ_(ω2)、β_(2)和β^(*)交互作用的影响显著,模型系数α_(1)、β^(*)、β_(2)、σ_(ω2)最佳组合为0.3052、0.0611、0.0826、0.853。最后通过试验验证合理性,结果表明模型系数最佳组合能较好地提高模拟计算准确性。In order to accurately simulate the turbulent non-equilibrium flow,Fluent software was employed to analyze the influence of the k-ωSST turbulence model coefficient on the simulation accuracy of the static pressure at the outlet of the exhaust diffuser of the high altitude platform.The model coefficient was then optimized using a response surface test.The results indicate:with the increase ofα_(1),the simulation accuracy initially increases and then decreases,stabilizing at 0.341.The gradual increase ofβ^(*)brings the simulation value closer to the target value,thereby improving accuracy.When the simulation value exceeds the target value,the accuracy first decreases and then increases;conversely,when the simulated value is less than the target value,accuracy decreases sharply.The increase ofβ_(2)also makes the simulation value gradually closes to the target value,thereby improving accuracy,when the simulated value is less than the target value,accuracy decreases sharply.Furthermore,the increase ofσ_(ω2)rapidly brings the simulation value close to the target value and improves accuracy.However,when the simulation value is less than the target value,the accuracy decreases slowly.Furthermore,the optimal ranges for the model coefficientsα_(1),β^(*),β_(2),andσ_(ω2)are from 0.2973 to 0.325,from 0.056 to 0.098,from 0.0756 to 0.089,and from 0.69 to 1.1984,respectively.Based on this,a significant sensitivity analysis through response surface experiments reveals that the order of sensitivity isα_(1)>β_(2)>β^(*)>σ_(ω2).The interaction effects ofβ^(*)withα_(1),α_(1)withσ_(ω2),andβ_(2)withβ^(*)are found to be significant.The best combination of model coefficientsα_(1),β^(*),β_(2)andσ_(ω2)is determined to be 0.3052,0.0611,0.0826 and 0.853.The best combination of model coefficients effectively improves the accuracy of simulation calculations,as demonstrated by the validation of experimental rationality.

关 键 词：k-ωSST湍流模型系数 不确定性 高空台排气扩压器 数值模拟 响应面试验 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]