Abstract: For improving the effectiveness of axial compressor blade aerodynamic design, an axial compressor blade aerodynamic optimization design process based on the quasi three-dimensional approach is developed, which combines blade quasi three-dimensional approach with profile automatic optimization technique. Radial distribution of loss data from blade three dimensional calculation is fed back to S₂ flow surface calculation, for replacing the original loss model based on the test data. With through-flow redesign, more precise calculation on S_2flow surfaces is developed. Automatic optimization design method based on parallel genetic algorithm and turbine CFD is applied to blade profile design on S_1flow surface. Replacing artificial modulation of blade aerodynamic profiles with process of numerical optimization, the optimization method reduces the dependence of artificial experience. A radial stacking rotor blade of axial compressor first stages is designed using the design process above. With total pressure ratio objective of 2.07and mass flow-rate objective of 6.3kg/s, rotor designed shows isentropic efficiency about 90%, and reaches stall margin of 15.5%. The proximity of objectives from throughflow design is satisfactory,too. Sweeping-bending design is conducted with 3D numerical optimization, which shows that the efficiency increase by 1% from the stall point to the working point.

Key words: Quasi three-dimenslonal design；Blade profile on S_1flow surface；Optimization design；Loss model of S_2flow surface；Axial compressor

摘要： 为提高轴流压气机叶片气动设计效果,将叶片准三维设计方法与叶型自动优化技术相结合,构建轴流压气机叶片准三维自动优化设计平台。在叶片三维数值计算结果中提取总压损失系数径向分布,反馈到S₂流面计算程序,替代原有的基于试验数据的损失模型,重新进行通流设计,提高S₂流面流场计算精度；S₁流面叶型设计采用并行遗传算法与叶轮机CFD方法相结合的叶型自动优化方法,以数值寻优代替叶型气动外形的人工调整,减小对设计经验的依赖。运用设计平台,对一设计流量6.3kg/s,设计压比2.07的轴流压气机第一级转子进行气动设计,得到径向三维叶片,设计点流量、总压比均接近设计目标,等熵效率接近90%,失速裕度达15.5%,结果令人满意。采用三维优化方法进一步进行叶片积叠线弯、掠设计,在失速点到设计点的稳定工作范围内效率均得到了1%的提升。 

关键词: 准三维设计;S₁流面叶型;优化设计;S₂损失模型;轴流压气机 