Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects

LI Bin; CHU Shibo; ZHA Hao; HE Xu

doi:10.7638/kqdlxxb-2025.0115

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Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects

更新时间：2026-05-28

- Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects
- Vol. 43, Issue 8, Pages: 119-129(2025)
- 作者机构：
  
  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. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0115
  CLC： TK47;V211.3
- Published：2025
- 稿件说明：
移动端阅览
李彬, 储世博, 查浩, 等. 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.

LI Bin, CHU Shibo, ZHA Hao, et al. Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects[J]. 2025, 43(8): 119-129.
李彬, 储世博, 查浩, 等. 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. DOI： 10.7638/kqdlxxb-2025.0115

LI Bin, CHU Shibo, ZHA Hao, et al. Research on the aerodynamic performance of compressor blades considering fluid-structure interaction effects[J]. 2025, 43(8): 119-129. DOI： 10.7638/kqdlxxb-2025.0115.

摘要

为精确量化跨声速叶片气弹耦合效应并揭示其流动机理，本文使用自研流固耦合仿真软件AENS，对NASA Rotor 67跨声速风扇叶片进行流固耦合分析。通过分析跨声速转子叶片静气动弹性变形，分离叶片关键形变参数，进一步研究叶片变形对静气动性能的影响。结果表明，在离心载荷和气动载荷的共同作用下，叶片变形主要为弯掠变形，且伴随安装角变化和径向变形。弯掠变形导致气流对叶片施加的载荷径向分量增大，分离区发展至叶尖后缘；安装角变化引起的攻角改变，导致高展长处的通道激波向上游移动；径向变形引起叶顶间隙的改变，泄漏涡夹角增大，变形后主泄漏流和二次泄漏流引起的损失增大。以上变形影响导致在近失速点处，变形后的总压比和绝热效率较静态叶片均有所降低，分别为1.18%和1.78%。研究验证表明，AENS软件在压气机流固耦合分析中展现出较好的预测精度，具有重要的工程应用价值。

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

Keywords

references

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