首页 | 本学科首页   官方微博 | 高级检索  
     检索      

1.5级跨声压气机中时序效应的研究
引用本文:任晓栋,顾春伟.1.5级跨声压气机中时序效应的研究[J].航空动力学报,2010,25(4):891-896.
作者姓名:任晓栋  顾春伟
作者单位:清华大学,机械工程学院,热能工程系,热科学与动力工程教育部重点实验室,北京,100084
基金项目:国家重点基础研究发展计划 
摘    要:以在建中的1.5级跨声压气机试验台所使用的压气机为研究对象,利用计算流体力学方法对其内部时序效应进行了研究.研究表明:静叶尾迹与出口导叶边界层中低能流体发生掺混时,掺混损失小,压气机效率高;静叶尾迹与出口导叶主流区中的高能流体掺混时,掺混损失大,压气机效率低,且最高效率与最低效率相差约0.4%;入口导叶与静叶间时序效应不明显.此外,得出了静叶-出口导叶轴向间隙与静叶-出口导叶间最佳时序位置的关系曲线.

关 键 词:跨声压气机  时序效应  非定常  尾迹  掺混
收稿时间:4/1/2009 12:00:00 AM
修稿时间:2009/6/15 0:00:00

Investigation on clocking effect of 1.5-stage transonic compressor
REN Xiao-dong and GU Chun-wei.Investigation on clocking effect of 1.5-stage transonic compressor[J].Journal of Aerospace Power,2010,25(4):891-896.
Authors:REN Xiao-dong and GU Chun-wei
Institution:Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, School of Mechanical Engineering, Tsinghua University, Beijing 100084, China;Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Department of Thermal Engineering, School of Mechanical Engineering, Tsinghua University, Beijing 100084, China
Abstract:The clocking effect in the 1.5-stage compressor, which would be used in the 1.5-stage transonic compressor test rig, was investigated by computational fluid dynamics (CFD) method in this paper. The results show that: (1) The compressor efficiency is high and mixing loss is low when the stator wake is mixed with the outlet guide vane (OGV) boundary-layer fluid. (2) The compressor efficiency is low and mixing loss is high when the stator wake is mixed with the OGV main flow area fluid. (3) The highest efficiency is 0.4% higher than the lowest efficiency. (4) The inlet guide vane (IGV)-stator clocking effect can be neglected, just leading to 0.025%0 improvement of compressor efficiency. Besides, the op-timal clocking position versus the stator-OGV axial clearance plot was got.
Keywords:transonic compressor  clocking effect  unsteady  wake  mixing
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号