基于RSM的带有热障涂层气膜孔参数优化的数值研究  

Numerical study on parameter optimization of the film hole with thermal barrier coating based on RSM

作　　者：闫浩楠 张丽[1] 朱惠人[1,2] 刘存良[1,2] 何爱杰 刘松 YAN Haonan;ZHANG Li;ZHU Huiren;LIU Cunliang;HE Aijie;LIU Song(School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China;Shaanxi Key Laboratory of Thermal Sciences in Aero-engine System,Northwestern Polytechnical University,Xi’an 710129,China;Sichuan Gas Turbine Establishment,Aero Engine Corporation of China,Chengdu 610500,China)

机构地区：[1]西北工业大学动力与能源学院,西安710129 [2]西北工业大学陕西省航空动力系统热科学重点实验室,西安710129 [3]中国航发四川燃气涡轮研究院,成都610500

出　　处：《航空动力学报》2023年第6期1328-1339,共12页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅲ-0001-0025);国家科技专项重点基础研究项目(2017-JCJQ-ZD-031-00)。

摘　　要：为解决有涂层时多种因素导致气膜冷效优化计算成本增大的问题,通过Box-Behnken方法合理设计3个吹风比(0.5、1.0和1.5)下,气膜孔流向倾角、长径比和涂层厚度3种参数的耦合模型,利用Realizable k-ε湍流模型进行数值模拟,将模拟结果通过响应面分析法(RSM)得到响应方程,最终通过响应方程预测最优参数。结果表明:孔倾角和涂层厚度为影响有涂层(TBC)气膜孔冷效的主要因素,长径比为影响冷效的次要因素。通过响应方程预测能达到最优气膜冷效时的模型,结果显示优化模型在所研究吹风比范围内气膜冷效相对于参考提升了55.45%~90.95%,响应方程的预测误差范围为2.71%~13.42%,具有较高的准确性。In order to solve the problem that many factors may lead to the increase of calculation cost of optimizing air film cooling efficiency,a coupling model of flow angle,length-diameter ratio and coating thickness at three blowing ratios(0.5,1.0 and 1.5)was reasonably designed by Box-Behnken design method.Realizable k-εturbulence model was used for numerical simulation.Response Surface Methodology(RSM)was used to analyze the simulation results to obtain the response equation,finally the optimal parameters were predicted by the regression equation.Researches showed that flow angle and coating thickness are the main factors affecting the cooling efficiency of film holes with thermal barrier coating(TBC),and the length-diameter is the secondary factor affecting the cooling efficiency.The response equation was used to predict the optimization model with best film cooling efficiency.Within the studied blowing ratio range,the results showed that the film cooling efficiency of the optimized model was 55.45%-90.95% higher than that of the reference,and the prediction error range of the response equation was 2.71%-13.42% with higher accuracy.

关 键 词：气膜冷却 热障涂层 长径比 响应面分析 几何参数 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]