基于拓扑优化的航空发动机叶片气动优化方法

  • 杨心源 ,
  • 邱若凡 ,
  • 米栋 ,
  • 周涛 ,
  • 周康 ,
  • 尤延铖 ,
  • 魏巍
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  • 1. 厦门大学
    2. 中航工业航空动力机械研究所
    3. 厦门大学航空航天学院
    4. 中国航发湖南动力机械研究所

收稿日期: 2025-12-01

  修回日期: 2026-02-13

  网络出版日期: 2026-02-27

基金资助

国家自然科学基金面上项目

Aerodynamic design method for aero-engine blades based on topology optimization

  • YANG Xin-Yuan ,
  • QIU Ruo-Fan ,
  • MI Dong ,
  • ZHOU Tao ,
  • ZHOU Kang ,
  • YOU Yan-Cheng ,
  • WEI Wei
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Received date: 2025-12-01

  Revised date: 2026-02-13

  Online published: 2026-02-27

摘要

航空发动机压气机与涡轮的气动优化是提升整机性能的关键。目前主流气动优化方法只能通过改变形状提升性能,而拓扑优化不受形状变化的限制,可在整个设计域内寻求最优的任意气动布局与形状。针对航空发动机叶片设计发展了两种拓扑优化方法:一是基于变密度的可压缩湍流流体拓扑优化方法,在常规变密度思路的流体拓扑优化方法基础上进一步考虑可压缩湍流特性,在常规变密度流体拓扑优化方法基础上进一步考虑可压缩与湍流特性,设计变量遍布整个设计空间的网格点上,通过离散伴随的方式实现了适用于亚声速到超声速的流体拓扑优化,应用于涡轮叶片与转子叶顶间隙构型,提升了涡轮效率;二是形状-拓扑参数化流体拓扑优化方法,全新提出一种基于“气动基元体+拓扑因素”思想的流体拓扑优化技术路线,以叶型作为基本单元,再将拓扑因素参数化,将形状与空间拓扑参数共同作为设计变量,有效规避了变密度方法的流-固交界面模糊、伴随方程求解稳定性等难题,通过压气机叶栅通道优化,生成的拓扑布局气动构型有效降低了总压损失。

本文引用格式

杨心源 , 邱若凡 , 米栋 , 周涛 , 周康 , 尤延铖 , 魏巍 . 基于拓扑优化的航空发动机叶片气动优化方法[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33165

Abstract

Aerodynamic optimization of compressor and turbine components is essential for enhancing aero-engine performance. While conventional shape-based optimization offers limited improvements, topology optimization explores the entire design space to identify optimal aerodynamic layouts beyond predefined geometries. This work presents two advanced topology optimization frameworks for blade design. First, a density-based approach incorporating compressible turbulent flow physics, with variables defined over the design domain, a discrete adjoint method enables efficient sensitivity analysis, yielding physically consistent configurations from subsonic to supersonic conditions, this method applied to turbine blades and tip clearance regions demonstrates notable efficiency gains. Second, a shape–topology parameterization method is introduced, building on the concept of “aerodynamic elements + topological factors.” Using blade profiles as foundational elements, the approach parameterizes both geometric and topological variables, avoiding the ambiguous fluid–solid interfaces and adjoint convergence issues of density-based methods. Optimized compressor cascades designed with this method exhibit reduced total pressure loss. This study broadens the paradigm for aerodynamic design for blades, offering new pathways toward high-performance next-generation aero-engines.

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