现代高性能轴流压缩机叶型机理和设计系统研究

Industrial axial compressors are essentially required of high efficiency.but also a wide operating flow range. Numerically generated blade profile through.transient flow field calculation can effectively prevent flow separating from the.blade surface, a use of such kind of blades will help to extend operating flow range.and enhance overall efficiency of the compressors. The present project focuses on.flow mechanism and dynamics of blade boundary layer, and it aims at developing a.advanced blade design system. It is of significance for the development and.advancement of axial flow compressor technology in China..At this phase of study, numerical approaches to multistage-axial-flow compressor.performance were established and validated experimentally, and they will be used.in blade-profile design for simulating a multistage environment; vortex method wasdeveloped to simulate the dynamic behaviour of blade boundary layer flow and willbe improved further; global optimization method was developed. Some obtainedresults were published in a journal paper. One Master student work full time andtwo PhD students part time on this project.

工业用轴流压缩机既要有高的效率又要有宽广的压比和流量变化范围。基于非稳定流场计算设计的叶型，能有效地控制叶面边界层分离，它的应用可以有效地拓宽压缩机稳定运行范围并提高效率。在国内该领域的研究尚属空白。本项目将在叶面边界层动态特性机理研究的基础上，建立一套现代叶型自动设计系统。为推动我国轴流压缩机技术的发展做贡献。