针对S2流面求解的通流计算方法与全三维黏性求解的计算流体力学(computational fluid dynamics,CFD)方法是叶轮机械气动设计与分析的主要技术手段。该文基于一套自主开发的流线曲率法通流计算程序,建立了适用于多级高负荷轴流压气机的通流与CFD一体化优化设计方法。该方法由通流与CFD一体化气动分析方法和基于改进智能优化算法的设计优化方法构成。研究将其应用于某跨音三级压气机中,对其中的跨音动叶边界层分离流动问题进行合理定位。针对第一级动叶(R1)与第三级动叶(R3)开展优化设计,分别获得了三级压气机效率提升0.1%和0.3%的优化设计方案。研究表明,该方法能够实现通流与CFD分析方法优势互补,同时把握气动布局设计与细节流场结构特征,从而高效定位压气机气动性能与流场结构问题及其与叶型设计或气动布局的关联,指导优化设计方向。
Abstract
Through-flow and computational fluid dynamics (CFD) calculations are the main approaches used for aerodynamic design and analyses of turbomachinery. In this study, an integrated through-flow and CFD optimization design method using an in-house through-flow code was used to analyze highly loaded multi-stage axial compressors. This method uses a multi-level aerodynamic analysis process that combines the through-flow and CFD calculations in a design optimization process that combines 3D blade design and intelligent optimization algorithms. The method is applied to a 3-stage transonic compressor and reasonably categorizes the flow problems resulting from the boundary layer separation along the transonic rotors. The analysis is used to optimize the first rotor (R1) and third rotor (R3) designs with the optimized designs giving 0.1 percent point and 0.3 percent point increases in the efficiencies of the 3-stage compressor. This study shows that this method is capable of synthesizing the advantages of the through-flow and CFD methods to simultaneously consider the characteristics of the aerodynamic configuration and flow structures. The compressor flow fields and performance can be efficiently categorized based on their relationships to the blade profile and aerodynamic configurations to provide guidance on how to optimize the design.
关键词
轴流压气机 /
通流计算方法 /
优化设计 /
跨音压气机 /
边界层分离
Key words
axial compressors /
through-flow calculations /
optimization /
transonic compressors /
boundary layer separation
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基金
任晓栋,副研究员,E-mail:rxd@mail.tsinghua.edu.cn
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