摘要
开展高压涡轮叶尖间隙变化规律及对应排气温度的影响规律研究,掌握发动机性能衰减情况并开展相应的结构优化,对提升发动机性能保持能力具有重要意义。通过分析某型发动机分解过程实测高压涡轮间隙数据,得到间隙随工作时间的变化规律,并将间隙与实测排气温度进行对比,得到间隙对排气温度的影响规律,在此基础上提出高压涡轮间隙控制结构优化方法。得到的结论为发动机工作初期,间隙快速增大,累计工作时间500~800 h后间隙趋于稳定,间隙增量约为0.41 mm。发动机累计工作前1000~1500 h,排气温度主要受间隙影响增加,间隙增大0.25 mm,对应排气温度增大21℃。1000~1500 h后,排气温度受其他因素影响继续增加,但增速减缓。
Change of high-pressure turbine clearance and its effects on exhaust temperature can be studied,performance attenuation of an aeroengine can be analyzed,and the corresponding structure can be optimized,which are significantly meaningful for restraining performance attenuation of the aeroengine.In this paper,change of high-pressure turbine clearance for an aeroengine with working time was obtained by analyzing data from actual measurements of clearance during disassembly of the aeroengine.Furthermore,effects of the clearance on exhaust temperature were analyzed by comparison the clearance with measured exhaust temperature.Finally,a control method of the clearance structure was proposed.Results show that the clearance increased rapidly at an initial stage,and thereafter tended to be stable when working time added up to about 500~800 h.Increment of the clearance was about 0.41 mm at the moment.Before working time of the aeroengine was accumulated from 1000 to 1500 h,increase of exhaust temperature mainly caused by increase of the clearance.The clearance increased by 0.25 mm,and the corresponding exhaust temperature increased by 21℃.With the working time further increased,the exhaust temperature increased due to other factors,but the increasing speed slowed down.
作者
徐丹
张清
霍枫
李娜
XU Dan;ZHANG Qing;HUO Feng;LI Na(The Second General Design Department of Aero-engine,AECC Shenyang Engine Design and Research Institute,Shenyang 110015,China)
出处
《沈阳航空航天大学学报》
2022年第1期24-28,共5页
Journal of Shenyang Aerospace University
基金
国家重大专项(项目编号:******)。
关键词
航空发动机
性能衰减
高压涡轮间隙
排气温度
叶尖间隙控制
aeroengine
performance attenuation
clearance of high-pressure turbine
exhaust temperature
clearance control
