空气动力学学报2025，Vol.43Issue(8)：119-129,11.DOI:10.7638/kqdlxxb-2025.0115
考虑流固耦合效应的压气机叶片气动性能研究
Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects
李彬 1储世博 2查浩 2何旭3
作者信息
- 1. 中国空气动力研究与发展中心计算空气动力研究所,绵阳 621000
- 2. 四川天府流体大数据研究中心,成都 610000
- 3. 中国空气动力研究与发展中心计算空气动力研究所,绵阳 621000||空天飞行空气动力科学与技术全国重点实验室,绵阳 621000
- 折叠
摘要
Abstract
To precisely quantify the aeroelastic coupling effects in transonic blades and reveal their flow mechanisms,this study employs the self-developed fluid-structure interaction(FSI)simulation software AENS to analyze the FSI characteristics of the NASA Rotor 67 transonic fan blade.By analyzing the static aerodynamic elastic deformation of transonic rotor blades,key deformation parameters of the blades were resolved to further investigate the influence of blade deformation on static aerodynamic performance.Results indicate that blade deformation under combined centrifugal and aerodynamic loads manifests primarily as bending-sweep deformation,accompanied by changes in the installation angle and radial deformation.The bending-sweep deformation increases the radial component of the aerodynamic load,causing the separation zone to expand from the leading edge to the trailing edge near the blade tip.The change in incidence angle shifts the channel shock upstream at high spanwise locations.Radial deformation alters the tip clearance,increasing the tip leakage vortex angle and exacerbating losses induced by primary and secondary leakage flows.Collectively,these effects reduce the total pressure ratio and adiabatic efficiency by 1.18%and 1.78%respectively at near-stall conditions compared to the rigid blade.Validation confirms that AENS demonstrates good predictive capability in compressor FSI analyses,highlighting its significant engineering value.关键词
流固耦合/叶片弹性变形/静气动性能/压气机叶片Key words
Fluid-structure interaction/elastic deformation of blade/static aerodynamic performance/compressor blade分类
能源科技引用本文复制引用
李彬,储世博,查浩,何旭..考虑流固耦合效应的压气机叶片气动性能研究[J].空气动力学学报,2025,43(8):119-129,11.
