超高速微尺度偏心转静间隙压力和温度场实验测量研究  

Experimental measurement of pressure and temperature field of micro-scale gap between eccentric rotator and stator at ultra-high rotational speed

作　　者：吕元伟 王仁轩 张镜洋[1] 刘源 黄璞 黄钟文 张鹏 LYU Yuanwei;WANG Renxuan;ZHANG Jingyang;LIU Yuan;HUANG Pu;HUANG Zhongwen;ZHANG Peng(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;AVIC Nanjing Engineering Institute of Aircraft Systems,Nanjing 210000,China;First Military Representative Office,Department of Air Force Equipment,Shanghai 201109,China)

机构地区：[1]南京航空航天大学航天学院,江苏南京210016 [2]航空工业金城南京机电液压工程研究中心,江苏南京210000 [3]空军装备部驻上海地区第一军代室,上海201109

出　　处：《推进技术》2025年第3期204-214,共11页Journal of Propulsion Technology

基　　金：国家自然科学基金(52206091);中国航空基金(201928052008);江苏省自然科学基金(BK20210303);航空动力创新工作站基金(HKCX2022-01-001)。

摘　　要：为探索超高转速下微尺度转静间隙剪切流动及热特性,本文进行了直径D=50 mm,转速n=0~6×10^(4) r/min,间隙比δ=0.0023,偏心率ε=0.62工况下转静间隙全向压力与气动热温升分布实验研究。通过复测和转轴轴心轨迹实时监控获得修正后的转静间隙尺度和偏心率。结果表明,微米尺度间隙耦合超高转速下,间隙气膜压力随时间呈现周期性分布规律且最大间隙区域的压力脉动幅度大于最小间隙。中心截面气膜压力沿周向呈现正弦分布趋势,但微尺度耦合超高转速使得最大正压值和最大负压值发生的区域更加靠近。有限长度转静间隙内的压力受到自作用轴向压差下端泄效应的影响,气膜压力沿轴向由中心截面向轴端逐渐降低。转速n>3×10^(4) r/min工况下,转静间隙剪切流气动热效应开始变得显著,到n=6×10^(4) r/min工况下,间隙气膜最大温升可达35℃。由于间隙两端受限情形不同,沿轴线方向最大压力和气动热温升位于中轴线偏向电机一侧区域附近且沿两侧逐渐降低。本文发现转静间隙气动热温升沿周向几乎相等,与已发表的研究呈现不同的规律。To investigate the micro-scale shearing flow and thermal characteristics of the rotor-stator clear⁃ance at ultra-high rotational speeds,this study conducted an experimental study on the distribution of the allaround pressure and aerodynamic heating temperature rise of the rotor-stator clearance under the working condi⁃tions of a diameter of D=50 mm,rotational speed of n=0~6×10^(4) r/min,clearance ratio ofδ=0.0023,and eccen⁃tricity ofε=0.62.The corrected clearance scale and eccentricity were obtained through repeated measurements and real-time monitoring of the axis trajectory.The results showed that under the coupling of ultra-high rotational speed andμm-scale clearance,the pressure of the clearance air film exhibited a periodic distribution pattern over time,and the pressure fluctuation amplitude in the region of maximum clearance was greater than that in the region of minimum clearance.The center section air film pressure exhibited a sinusoidal distribution trend along the circumferential direction,but the coupling of micro-scale and ultra-high rotational speed caused the regions of maximum positive pressure and maximum negative pressure to be closer to each other.The pressure inside the finite-length rotor-stator clearance was affected by the downstream leakage effect of the self-acting axial pressure difference,and the air film pressure gradually decreased along the axis from the center section to the axial end.Under the working condition of n>3×10^(4) r/min,the aerodynamic heating effect of the rotor-stator clearance began to become significant,and at the working condition of n=6×10^(4) r/min,the maximum temperature rise of the clear⁃ance air film could reach 35℃.Due to the different confinement conditions at both ends of the clearance,the maximum pressure and aerodynamic heating temperature rise along the axial direction were located near the re⁃gion,where is more close to the motor side,and then gradually decreased along the axial direction.It is found that the aerodynamic heating tempera

关 键 词：剪切流动 转静间隙 压力测量 气动热测量 微尺度间隙 端泄效应 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]