多级轴流压气机级间性能试验研究  

Experimental Research on Inter-Stage Performance of Multistage Axial Flow Compressor

作　　者：杨灵[1] 温珍荣[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703

出　　处：《燃气涡轮试验与研究》2012年第4期12-15,7,共5页Gas Turbine Experiment and Research

摘　　要：对某多级轴流压气机级间性能进行试验研究,详细分析了该压气机在设计角度与优化角度下,不同工况时的性能特性(包括各级做功能力、级压比和不稳定边界变化规律等)和级间匹配情况。研究结果表明,在非设计状态下各级匹配可以进一步优化、改进设计;进口静叶角度变化会改变压气机的级负荷分配和级不稳定边界位置,影响压气机不稳定边界移动。建议适当开大一、二级静叶角度,以改善二、三级转子流场,提高其性能;同时,应在不影响整台压气机不稳定边界的情况下进行静叶角度优化。Experimental research on the inter-stage performance of a multistage axial flow compressor was made. Its performance characteristics, such as the working ability at different conditions, stage pressure ra- tio, unsteady boundary variation law and the matching between stages with design angle and optimized an- gle were analyzed. The test results showed that the matching between stages can be further optimized under off-design conditions. Meanwhile, the variation of the vane angle at inlet would change the load distribution and the location of the unsteady boundary, which would cause the moving of the unsteady boundary of the compressor. It is suggested that the first and second vane angle could be enlarged appropriately to improve the flowfield of the second and third rotor to enhance the performance; at the same time, vane angle should be optimized without affecting unsteady boundary of whole compressor.

关 键 词：轴流压气机 级间性能 静叶角度 不稳定边界 

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]