跨声速轴流压气机多叶排反问题优化方法  

Optimization of Transonic Axial Compressor Using Multi-Row Inverse Method

作　　者：刘昭威 吴虎[1] 唐晓毅[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《西北工业大学学报》2016年第1期118-124,共7页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(51076131)资助

摘　　要：为提升跨声速压气机的气动性能,以叶轮机械三维黏性反问题设计理论为基础,发展了适用于压气机多叶排三维反问题优化设计方法。描述了压气机多叶排流场计算所采用的数值求解技术,详细推导了反问题优化设计方法和流程。为验证方法的正确性,运用德国宇航中心单级跨声速压气机R030-SUKS/31的实验数据与计算结果进行对比。在对原型叶片表面载荷进行分析的基础上,重新修改叶片表面载荷分布,并通过反问题设计方法计算得到新的叶片几何构型。结果表明,通过修改叶片表面载荷分布,运用反问题设计方法得到的压气机,其进口相对马赫数有所提升,压气机流量和压比分别提高了3.5%和2.0%,气动性能有明显提升,验证了方法的正确性和有效性。In order to improve the aerodynamic performance of transonic compressor, a compressor inverse design program is developed based on the turbomachnary three-dimensional viscous inverse design method theories. The numerical solution methods of Multi-Row transonic axial compressor flow field are introduced first and then the in- verse design method and process is described in detail. The DLR R030-SUKS/31 single-stage transonic axial com- pressor experimental data are used to validate the calculation results. On the basis of the analysis of original blade loading distribution, the blade geometry is redesigned by applying the inverse method with the modified loading dis- tribution. The numerical results show an increase in the compressor inlet Mach number. The mass flow rate and pressure ratio are increased respectively by 3.5% and 2.0%. Better performance of the redesigned compressor is a- chieved; this demonstrates the effectiveness of this method.

关 键 词：反问题设计方法 载荷分布 优化设计 跨声速压气机 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]