不同展向位置非连续鼓包对跨声速压气机转子性能的影响
Effect of Discontinuous Bump at Different Spanwise Positions on the Performance of Transonic Compressor Rotor
杨嗣涵 1杨旭东 1韩吉昂 1郭重佳1
作者信息
- 1. 大连海事大学船舶与海洋工程学院,大连 116026
- 折叠
摘要
为提高跨声速压气机气动性能,本文针对NASA Rotor 37,采用数值模拟方法研究了吸力面不同展向位置非连续鼓包对其气动性能的影响.结果表明,随着非连续鼓包逐渐靠近叶顶,鼓包能更有效地对激波前气体进行预压缩,降低逆压梯度,从而减小激波强度.同时对于激波与附面层的相互作用的抑制效果也逐渐增强,能有效地使激波干扰所产生的附面层分离延后,改善流动情况,降低损失.相比原型转子,在60％～90％叶高范围布置非连续鼓包时,压气机转子效率在整个流量范围内均有提升,最高效率增加了0.25％,总压比提升了0.13％.
Abstract
In order to improve the aerodynamic performance of the transonic compressor,this paper uses numerical simulation methods to study the effect of discontinuous bump at different spanwise positions on the aerodynamic performance of NASA Rotor 37.The results indicate that as the discontinuous bump gradually approaches the blade tip,the bump can more effectively pre-compress the flow before the shock wave,reduce the reverse pressure gradient,and thus reduce the shock wave intensity.At the same time,the inhibitory effect on the interaction between the shock wave and the boundary layer is gradually increasing,which can effectively delay the separation of the boundary layer caused by the shock wave interference,improve the flow situation,and reduce losses.Compared to the prototype rotor,when discontinuous bump are arranged at 60％～90％blade height,the efficiency of the compressor rotor is improved throughout the entire flow range,with the highest efficiency increasing by 0.25％.At the highest efficiency,the total pressure ratio of the prototype blade is increased by 0.13％.
关键词
跨声速压气机转子/非连续鼓包/展向位置/气动性能/数值模拟Key words
transonic compressor rotor/discontinuous bump/spanwise position/aerodynamic per-formance/numerical simulation引用本文复制引用
基金项目
国家自然科学基金重点项目(52236005)
航空发动机及燃气轮机基础科学中心重点项目(P2022-B-Ⅱ-007-001)
出版年
2024
NETL
NSTL
维普
万方数据