雷诺数效应对小流量多级轴流压气机的性能影响  

Effects of Reynolds Number in a Small Multistage Axial Flow Compressor

作　　者：温泉[1] 梁德旺[1] 李逢春[2] 陈国智[2] 涂孟罴[2] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2004年第1期81-88,共8页Journal of Aerospace Power

摘　　要：通过试验和数值模拟,对一台设计压比为6,效率0.84的小流量轴流压气机进行了雷诺数效应的分析和研究。介绍了这台压气机在设计转速下的性能曲线、不同雷诺数下折合转速n=0.85的试验结果,以及二维平面叶栅和三维数值模拟分析结果。试验和数值模拟的分析表明,随着雷诺数降低,会增加附面层厚度,改变压气机的三维流场结构,降低压气机的性能。根据折合转速n=0.85的试验和数值模拟分析结果,对这台压气机在折合转速n=1.0性能进行了雷诺数修正。The effect of Reynolds number in small multistage axial flow compressors is described and illustrated by experimental data and numerical simulation for a four-stage axial flow compressor, of which total pressure ratio is 6.0 and polytropy efficiency is 0.84 at design points. The performance of this compressor is obtained at 100 percent of the rotational speed. The influence of variations in flow Reynolds number has been studied through experimental data at 85 percent of the rotational speed. Using a three-dimension calculation code, the detailed flow-field of this compressor at different Reynolds Numbers has been obtained. The results show that the thickness of boundary layer increases with decreasing Reynolds number, mean while the flow-field structure is changed, and the performance of this compressor will be worse. Combined with experimental data and numerical simulation, the performance of this compressor has been modified using a correlation. Considering the effect of Reynolds number, the performance of this compressor will be that the total pressure ratio is 6.22 and polytropy efficiency is 0.85 at design rotational speed.

关 键 词：雷诺数效应 小流量多级轴流压气机 性能试验 数值模拟 平面叶栅 

分 类 号：TK401[动力工程及工程热物理—动力机械及工程] V231.3[航空宇航科学与技术—航空宇航推进理论与工程]