高转速大负荷多级轴流压气机试验排故分析与验证  

Experimental troubleshooting analysis and verification study of a multi-stage axial-flow compressor with high speed and load

作　　者：任飞[1] 徐峰[1] 张亚[1] 刘志刚[1] 向宏辉[1] 苏廷铭[1] 夏联[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》2016年第6期30-33,共4页Gas Turbine Experiment and Research

摘　　要：小型高速大负荷多级轴流式压气机设计中应用了多种先进技术,在其进行总性能参数录取前的机械运行试验中,试验件第一级转子叶片尖部出现多处裂纹。分别对试验现象和结构强度进行分析研究,得出叶片裂纹主要是由于叶片受激励后发生共振致使叶片出现高周疲劳所致。根据故障原因,对该型压气机试验件结构设计方案进行优化,并对优化试验件的总性能参数进行试验录取。结果表明,优化后的压气机试验件运行状态良好,且各项总性能指标表现优异,优化措施可行有效。Multiform advanced technologies were applied to the design of a multi-stage axial flow compres- sor, overall performance experiment was carried out for verification, and several cracks were found at the first stage rotor blade tip. The phenomena and structure intensity were analyzed and explored in the troubleshooting phase. Finally it was concluded that the crack was mainly caused by high cycle fatigue due to the blade resonant vibration. After then this compressor structure design was optimized to record overall performance parameters. It can be seen from the test results that after structure optimization the running state of the compressor is good and all index show its performance is excellent, proving that the optimization is feasible and effective.

关 键 词：航空发动机 高速轴流压气机 叶片裂纹 排故 试验验证 共振频率 高周疲劳 

分 类 号：V263.6[航空宇航科学与技术—航空宇航制造工程]