摘要
针对涡轮在理论设计和实际应用中存在的不足,提出了利用多学科优化平台对涡轮进行气动优化设计的方法。首先运用UG/Grip技术对涡轮进行三维造型,然后利用试验设计方法建立计算试验样本点分布表,用商用软件进行各样本点的CFD计算及热-应力耦合分析计算,最后建立响应面模型,对其进行优化设计。结果表明,优化后的涡轮效率比优化前提高5%。该方法为进一步提高涡轮的气动性能,减少损失提供了一定的依据。
To solve the problems of turbos, a multidisciplinary design optimization plat is presented. At first, UG/Open Grip technique was adopted to parameterize the turbo. Then, the sample point distribution was obtained by the experimental design method, With the help of software Fluent and Ansys, the efficiency and stress of every sample points can be get. Therefore, the response sur- face model can be built up on these results and an optimization algorithm was adopted on the re- sponse surface model. At last, the optimization turbo was obtained. The results indicate that the efficiency of the optimization turbo was increased by 5%. All results show the method is very important and available for improving the performance, reducing the loss, and others.
出处
《火箭推进》
CAS
2008年第2期13-17,共5页
Journal of Rocket Propulsion
关键词
涡轮
CFD计算
响应面
turbo
CFD calculate
response surface model
