摘要
为了抑制存在于压气机的角区分离现象,提高发动机的工作性能,基于NACA48-K65的压气机模型,设计了叶根自主引气射流模型结构。通过数值模拟,研究不同位置及不同高度比的叶根自主引气射流结构方案对压气机叶栅气动性能和流场结构的影响,确定最利于总压损失系数降低的方案。研究结果表明,开设叶根自主引气射流结构能够有效削弱吸力面壁面涡强度,抑制角区分离沿节距和叶高方向范围,降低叶栅的流动损失。开设位置的后移会导致控制效果减弱,高度比的增大使得抑制能力先增强后下降,最佳方案能够有效地将总压损失系数降低10.5%。
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%.
作者
徐文峰
李傲
孙丹
任国哲
黄士升
XU Wenfeng;LI Ao;SUN Dan;REN Guozhe;HUANG Shisheng(College of Aero-engine,Shenyang Aerospace University,Shenyang 110136,China;Key Laboratory of Advanced Test Technology for Aeronautical Propulsion System of Liaoning Province,Shenyang Aerospace University,Shenyang 110136,China)
出处
《沈阳航空航天大学学报》
2025年第1期36-44,共9页
Journal of Shenyang Aerospace University
基金
国家自然科学基金(项目编号:52075346)
辽宁省教育厅基本科研青年项目(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)。
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
blade root self-induced jet structure
compressor cascade
corner separation
flow field structure
total pressure loss
