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基于扭矩测量的轴流压气机效率评定方法研究

Efficiency evaluation method of axial compressor based on torque measurement
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摘要 为发展多因素影响下压气机全工况效率高精度试验评定方法,针对工程上扭矩法测量与评定压气机绝热效率中存在的问题,开展了前置齿轮箱供油润滑条件和轴承封严腔泄漏流对扭矩效率测量影响的试验研究。结果表明:提高齿轮箱供油压力或降低供油温度,均会增大齿轮箱机械损失,导致压气机扭矩效率测量结果偏低。试验过程中,应保证齿轮箱供油润滑条件的稳定,供油压力变化范围不大于20 kPa,供油温度变化范围不大于5℃。压气机轴承封严腔内气流会通过篦齿间隙向流道内泄漏,导致压气机进/出口流量发生不连续变化。进气节流比越小,气流泄漏量越大,扭矩效率测量结果越低。试验前应对压气机进行密封性检测。 To develop high precision experimental evaluation method of compressor under all working condi⁃tions with the influence of many factors,aiming at the problems existing in measuring and evaluating compres⁃sor adiabatic efficiency by torque method in engineering,the influence of lubrication conditions of front gear⁃box and leakage flow of bearing seal cavity on torque efficiency measurement was studied experimentally.The results show that increasing the oil supply pressure of gearbox or reducing the oil supply temperature will in⁃crease the mechanical loss of the gearbox and lead to the low measurement result of the compressor torque effi⁃ciency.During the experiment process,the stability of lubrication conditions of front gearbox should be en⁃sured,and the variation range of oil supply pressure should not exceed 20 kPa,and the variation range of tem⁃perature should not exceed 5℃.The air flow in the sealed cavity of the compressor bearing will leak into the flow passage through the labyrinth gap,resulting in discontinuous changes in the inlet and outlet flow of the compressor.The smaller the intake throttle ratio gets,the larger the air leakage flow and the lower the torque efficiency measurement result will be.Before the experiment,the compressor should be tested for tightness.
作者 向宏辉 侯宽新 刘宽 高杰 吴森林 赵正 张毅 XIANG Hong-hui;HOU Kuan-xin;LIU Kuan;GAO Jie;WU Sen-lin;ZHAO Zheng;ZHANG Yi(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China;Sichuan Province Engineering Technology Research Center of Turbomachinery of Aero-engine and Gas Turbine,Mianyang 621000,China;College of Aeronautical Engineering,Civil Aviation Flight University of China,Guanghan 618307,China)
出处 《燃气涡轮试验与研究》 2021年第4期1-6,共6页 Gas Turbine Experiment and Research
基金 民用飞机专项科研项目(MJ-2016-J-96) 国防基础军工科研院所稳定支持专项(GJCZ-0207-21)。
关键词 航空发动机 轴流压气机 扭矩效率 前置齿轮箱 进气节流比 泄漏流 试验研究 aero-engine axial compressor torque efficiency front gearbox intake throttle ratio leakage flow experimental investigation
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