沈阳航空航天大学学报2025，Vol.42Issue(1)：36-44,9.DOI:10.3969/j.issn.2095-1248.2025.01.004
叶根自主引气射流结构对压气机叶栅性能的影响
Influence of blade root self-induced jet structure on compressor cascade performance
摘要
Abstract
To suppress the corner separation phenomenon existing in the compressor and improve the working performance of the engine,based on the NACA48-K65 compressor model,the structure of the blade root self-induced jet structure was designed.By numerically simulating the influence of different opening positions and different height ratios of the blade root self-induced jet structure on the aerodynamic performance and flow field structure,the scheme most conducive to reducing the total pressure loss coefficient was determined.The results show that the blade root self-induced air jet structure can effectively weaken the vortex strength of the suction wall,suppress the corner separation along the pitch and blade height direction,and reduce the flow loss of the cascade.The backward movement of the opening position will lead to a gradual weakening of the control effect.Increasing the height ratio will increase the suppression capability first and then decrease it.The optimal scheme can reduce the total pressure loss coefficient by 10.5%.关键词
叶根自主引气射流结构/压气机叶栅/角区分离/流场结构/总压损失Key words
blade root self-induced jet structure/compressor cascade/corner separation/flow field structure/total pressure loss引用本文复制引用
徐文峰,李傲,孙丹,任国哲,黄士升..叶根自主引气射流结构对压气机叶栅性能的影响[J].沈阳航空航天大学学报,2025,42(1):36-44,9.基金项目
国家自然科学基金(项目编号:52075346) （项目编号:52075346）
辽宁省教育厅基本科研青年项目(项目编号:JYTQN2023069) （项目编号:JYTQN2023069）
辽宁省大学生创新创业训练计划支持项目(项目编号:D202311142250153835). （项目编号:D202311142250153835）
