非定常涡升力机制的三维效应
Three-Dimensional Effect of the Unsteady Vortex Lift Mechanism
王卓 1杜林 1孙晓峰1
作者信息
- 1. 北京航空航天大学航空发动机研究院,北京,100191
- 折叠
摘要
本文采用浸入式边界方法对一低速单级压气机在不同轴向间距下的转静干涉流动进行了数值模拟,主要关注缩小轴向间距后由于非定常涡升力机制所引起的前后排叶片流动状态变化.计算结果表明,级性能随间距出现提升的流动机理在于,当间距减小后,前排转子的负荷出现提升,这一变化使得级间静压升高,静子根部的逆压梯度得到有效的缓解,进而导致静子根部的流动分离被抑制,压气机的压升及效率均出现明显的提升.
Abstract
An Immersed Boundary(IB)method is employed to simulate the rotor/stator interaction flow for a low-speed compressor working at different axial stage gaps in this paper.The flow variation due to the unsteady-vortex mechanism induced by reducing the stage gap is investigated and the results reveal that one origin of the performance enhancement at a smaller gap is found to be the loading enhancement of the upstream rotor.This variation results in a higher intra-stage static pressure,which reduces the inversed pressure gradient around the hub of the stator and further suppresses the flow separation at this region.Therefore,both the pressure rise and efficiency of the compressor are found to be higher.
关键词
转静干涉/非定常涡升力/浸入式边界方法Key words
rotor/stator interaction/unsteady vortex lift/immersed boundary method引用本文复制引用
基金项目
国家自然科学基金项目(52022009)
中央高校基本科研业务费专项资金资助()
出版年
2024
NETL
NSTL
万方数据