高压比跨声速离心压气机设计研究  

Design and Study of High Pressure Ratio Transonic Centrifugal Compressor Stages

作　　者：高丽敏[1] 高磊[1] 谢建[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]中国航空动力机械研究所

出　　处：《风机技术》2016年第3期42-49,共8页Chinese Journal of Turbomachinery

基　　金：陕西省自然科学基金(2014JM7248);国家自然基金(51236006)

摘　　要：为探索高压比跨声速离心压气机级的快速设计方法,以级总压比7.0为目标,采用自行开发的离心压气机快速设计程序,设计了一单级跨声速离心压气机,并采用适应于高进口马赫数的低稠度最大厚度后移的双圆弧叶型叶片扩压器,保证压气机级有较宽的稳定工作流量范围。经CFD软件对设计的压气机进行性能预测表明,初步设计的离心压气机叶片扩压器扩张角过大,造成叶片尾缘出现严重回流。通过调整叶片厚度和中心线折转角减小了扩张角,改进后的离心压气机设计点总压比为8.305,等熵效率为81.8%。To investigate the rapid approach for designing transonic centrifugal compressor stages with high pressure radio, a single transonic centrifugal compressor stage was designed targeting a total pressure ratio of 7.The double arc cascade with maximum thickness near to the trailing edge was applied to meet the need of high Mach number inlet conditions within the diffuser. A low solidity diffuser is applied to guarantee a wide operational flow range. After the performance was predicted by CFD, it revealed that the excess divergence angle in the initial design of vaned diffusers caused serious reverse flow at the trailing edge of the blade. To improve stage performance, measurements have been taken by adjusting blade thickness and the deflected angle of camber line to reduce the divergence angle. At this design point, the total pressure ratio of the improved stage is 8.305 and isentropic efficiency is 81.8%.

关 键 词：离心压气机 跨声速叶轮 低稠度叶片扩压器 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程] TK05[动力工程及工程热物理]