摘要
针对压气机试验设备与试验件之间存在的气动耦合问题,探讨了压气机试验系统中影响试验对象性能评定的两类边界影响因素。通过构建理论分析模型,研究了进气系统压力损失对压气机试验特性的影响,和排气系统容腔效应对压气机过失速性能的影响。结果表明:(1)敞开吸气式压气机试验进气系统中流动损失最大的区域集中在进气节流阀处,依据各节流元件具体类型分段建立流动损失模型,可为间接获取压气机试验件进口压力参数提供新的自由度;(2)将试验设备排气节流装置直接布置在试验件流道出口,可抑制排气系统的容腔效应,保证压气机部件台架安装环境下的稳定性试验结果更趋近于整机工作环境;(3)相比于大流量风扇,高负荷多级压气机气动稳定性对于试验排气系统的容腔效应表现得更敏感。
Aiming at the aerodynamic coupling problem between the test specimen and the compressor rig,the effects of two kinds of boundary factors on the compressor performance evaluation were investigated.By constructing a theoretical analysis model,the effects of the total pressure loss of intake piping system on the compressor performance and the cavity of air exhaust system on the compressor post stall performance were studied.The results show that:①For the open air intake piping system,the maximum total pressure loss is focused on the throttle valve.The entire air intake piping system is divided into several throttling elements,then corresponding flow loss models is established separately,by this way the pressure parameters at the compressor inlet could be obtained indirectly.②When the throttling device is installed at the compressor outlet,it has a significant advantage in restraining the cavity effect of exhaust system to ensure that thesteady experimental results of the compressor at the experimental environment are close to the overall engine test data.③Compared to the fan with large mass flow,the aerodynamic stability of the high loaded multistage compressor is more sensitive to the cavity effects in the exhaust system.
作者
向宏辉
吴虎
高杰
刘昭威
葛宁
XIANG Hong-hui;WU Hu;GAO Jie;LIU Zhao-wei;GE Ning(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AECC Sichuan Gas Turbine Establishment,Jiangyou 621703,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)
出处
《燃气涡轮试验与研究》
北大核心
2017年第2期22-31,共10页
Gas Turbine Experiment and Research
基金
四川省应用基础研究项目(2017JY0040)
航空动力基金项目(6141B090303)
关键词
压气机试验系统
流动损失
排气容腔
性能特性
过失速
喘振
compressor test system
flow loss
exhaust plenum
performance characteristics
post stall
surge
