摘要
本文通过数值模拟研究了旋流畸变流场特性及其对压气机性能的影响。设计了可调安装角的叶片式旋流畸变发生器。对比不同几何参数条件下的流场发现,畸变发生器的叶片安装角和支撑环位置分别改变了下游旋涡的强度和空间位置,进而对旋流畸变的强度造成影响。不同位置叶片安装角主要影响当地流场的旋涡强度,并通过对旋涡间的相互耦合对其它区域的流场造成一定影响。支撑环位置的改变使得涡中心位置随之移动。随后分析了畸变发生器旋流畸变对某跨音1.5级压气机气动性能的影响,结果表明与均匀进气相比,旋流畸变导致稳定裕度相对减小了11.91%,但最高效率相对增加0.32%。进一步流场分析表明,旋流畸变主要改变了动叶进口气流角,从而造成稳定裕度衰减;而静叶总压损失减小使得效率有所增加。
This paper studies the swirl distortion flow field characteristics and its impact on com-pressor performance through numerical simulation methods.A blade-type swirl distortion generator with adjustable stagger angle was designed.Comparing the fow fields under different geometric parameters,it is found that the blade stagger angle and the support ring position of the distortion generator change the intensity and spatial position of the vortex respectively,which in turn affects the intensity of the swirl distortion.The stagger angle of blades at different positions mainly af-fects the vortex intensity of local fow field,and has a certain impact on the flow field in other areas through altering the coupling between vortices.The change in the position of the support ring causes the position of the vortex core.The impact of this swirl distortion on the aerodynamic performance of a 1.5-stage transonic axial compressor is then analyzed.Results show that the swirl distortion reduces the stability margin by 11.91%,but the maximum efficiency is relatively increased by 0.32%.Further flow field analysis shows that the swirl distortion mainly changes the inlet flow angle of rotor blade,thereby deteriorating the stability margin.However,the inlet distortion leads to reduction in the total pressure loss of the stator and hence increases the efficiency.
作者
连皓军
张敏
杜娟
巴顿
聂超群
LIAN Haojun;ZHANG Min;DU Juan;BA Dun;NIE Chaoqun(Digital Twin Research Center,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;Key Laboratory of Advanced Energy and Power,Chinese Academy of Sciences,Beijing100190,China;National Key Laboratory of Science and Technology on Advanced Light-duty Gas-turbine,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《工程热物理学报》
北大核心
2025年第9期2858-2868,共11页
Journal of Engineering Thermophysics
基金
国家自然科学基金青年科学基金项目(No.52206061)
国家重大科技专项(No.J2019-II-0017-0038)。
关键词
对涡旋流畸变
叶片
畸变发生器设计
压气机气动性能
twin swirl distortion
blade
distortion generator design
compressor aerodynamic performance
