叶型探针对轴流压气机性能试验结果的影响  

Effect of Airfoil Probes on the Experimental Results of Axial Flow Compressor Performance

作　　者：向宏辉[1] 任铭林[1] 马宏伟[2] 黄明镜[1] 樊嘉峰[1] 

机构地区：[1]中国燃气涡轮研究院,四川江油621703 [2]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《燃气涡轮试验与研究》2008年第4期28-33,共6页Gas Turbine Experiment and Research

摘　　要：基于近年来所录取的大量压气机试验数据,详细分析了叶型探针对轴流压气机各项性能参数的影响,并对某型低负荷轴流压气机进行了稳定性试验,比较了80%设计转速下压气机在安装叶型探针前后稳定裕度的变化。结果表明:叶型探针对轴流压气机设计与非设计状态性能均会产生一定的负面影响,对于静叶高度不低于20mm的轴流压气机,其性能数据测量误差范围约在2%以内;压气机级增压能力所受到的影响程度与流道堵塞比有关,堵塞比越大,级静压比下降越多;安装叶型探针后,压气机的失速点流量增加,稳定裕度降低。Based on a large number of compressor experimental data taken in recent years, this paper analyzed the influence of airfoil probes installed at the leading edge of stator row on the performance parameters of multistage axial compressors in detail. Stability experiment of a low load multistage axial compressor was also carried out to compare the stall margin changes with/without airfoil probe installation at 80% design speed. The results show that airfoil probes have a negative effect on the performance of compressor under both design and off design operating conditions. For multistage axial compressors with a minimum stator blade height over 20 millimeters, the total performance instrumentation error is approximately within 2%. The effect on stage pressure rise capacity is directly related to the blockage ratio by airfoil probes, with a larger blockage ratio, a heavier stage static pressure ratio loss. When airfoil probes are installed, the mass flow rate at stall point increases, this leads to the stall margin declining.

关 键 词：叶型探针 轴流压气机 堵塞比 性能 

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]