摘要
以单通道轴流压缩机rotor37为研究对象,合理设计了叶顶小间隙和周向槽,采用数值计算的方法,研究叶顶小间隙和周向槽耦合作用对轴流压缩机性能的影响。计算结果表明,可以在不降低效率的同时,有效地扩大压缩机的稳定裕度,提高压比。在此基础上,对其机理进行深入分析,认为适当减小间隙可以有效降低叶顶泄漏流,提高效率。周向浅槽由于增加径向流动,增加了损耗,但是可以改善压比和稳定裕度。两者的耦合作用,可以在不降低效率的同时,有效地扩大压缩机的稳定裕度。
Small Tip clearance and circumferential groove were applied to the axial-flow compressor rotor 37 by simulating flows in one blade channel.Numerical simulation method is used to study the influence of small tip clearance and circumferential groove coupling effect on performance of axial flow compressor.The results show that the stall margin of compressor can be effectively enlarged and pressure ratio can be improved while the efficiency is not reduced.Based on this method,this paper presents efficiency was increased by reasonable reducing blade tip clearance based on mechanism analysis.Stall margin,total pressure ratio and loss were increased by radial flow of circumferential groove.But efficiency was reduced.Not only stall margin and total pressure ratio were increased but also efficiency was not reduced by the coupling effects of small tip clearance and circumferential goove.
出处
《风机技术》
2014年第5期23-27,共5页
Chinese Journal of Turbomachinery
基金
国家自然科学基金重点项目(51236006)
关键词
跨音轴流压缩机
叶顶间隙
周向槽
transonic axial compressor
blade tip clearance
circumferential groove
