离心压气机叶片角分布对性能影响与规律研究

Study on the Influence and Laws of Blade Angle Distribution on the Performance of Centrifugal Compressor

摘要: 文章以一款离心压气机叶轮作为研究对象，使用CFD数值仿真方法研究了在叶尖与叶根叶片角分布形式变化时对离心压气机性能所带来的影响。研究表明：叶尖和叶根进口处叶片角变化越快，叶片喉道面积越宽，堵塞流量越往右移，且进口处载荷越大，叶轮总压比越小。叶尖最大载荷点的β值变化量在5˚内时，β值增大，堵塞流量微量右移，叶轮总压比会有小幅度的上升。叶根最大载荷点β值变化量在5˚内时，β值增大，堵塞流量快速右移，叶轮总压比明显上升。

Abstract: This paper takes an impeller of a centrifugal compressor as the research object, and uses the CFD numerical simulation method to study the effects of variations in the distribution forms of blade angles at the blade tip and blade root on the performance of the centrifugal compressor. The research shows that the faster the blade angle changes at the blade tip and blade root inlets, the wider the blade throat area, the further the choking flow shifts to the right, the greater the load at the inlet, and the smaller the total pressure ratio of the impeller. When the variation of the β value at the maximum load point of the blade tip is within 5˚, an increase in the β value leads to a slight right shift of the choking flow and a small increase in the total pressure ratio of the impeller. When the variation of the β value at the maximum load point of the blade root is within 5˚, an increase in the β value results in a rapid right shift of the choking flow and a significant increase in the total pressure ratio of the impeller.