Aerodynamic design of compressor blade using optimization algorithm

WANG Guang-wen; ZHOU Zheng-gui; HU Jun

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Aerodynamic design of compressor blade using optimization algorithm

更新时间：2026-07-07

- Aerodynamic design of compressor blade using optimization algorithm
- Vol. 23, Issue 7, (2008)
- 作者机构：
  
  南京航空航天大学能源与动力学院,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2008
- 稿件说明：
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WANG Guang-wen, ZHOU Zheng-gui, HU Jun. Aerodynamic design of compressor blade using optimization algorithm[J]. 2008, 23(7).
DOI：

WANG Guang-wen, ZHOU Zheng-gui, HU Jun. Aerodynamic design of compressor blade using optimization algorithm[J]. 2008, 23(7). DOI：

摘要

将数值最优化方法与叶轮机械正问题流场计算相结合

实现对风扇/压气机叶片积叠线、子午面流道和沿径向弦长分布组合的优化设计

数值最优化采用基于局域网的并行遗传算法.运用该软件对NASArotor67风扇转子进行重新设计

设计目标为设计点压比和流量不变、效率最高以及堵点流量不变.与原风扇转子比较

稳定工作流量范围略增大并且在整个工作流量范围内优化转子压比近于不变、效率提高约0.5个百分点.

Abstract

An automatic aerodynamic optimization system for axial compressor was constructed

which was composed of turbomachinery flow field simulations in3-D Navier-Stokes equation methods

grid automatic generations

parameterizations of blade profiles

meridional channels and stacking line and the advanced parallel genetic algorithm based on intranet.In construction of objective functions

design point adiabatic efficiency

mass flow rates

pressure ratio and non-design point mass flow rates was considered.NASArotor67 was redesigned using the optimization system

and the present method successfully obtained a design that improved adiabatic efficiency by 0.5% compared with the rotor67 while satisfying mass flow rate and pressure ratio.

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Related Author

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Lucheng JI

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Wei WEI

Siyuan REN

Husheng MA

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Related Institution

Nanjing University of Aeronautics and Astronautics

School of Aerospace Engineering，Beijing Institute of Technology

Institute for Aero Engine，Tsinghua University

Aerospace Technology Institute，China Aerodynamics Research and Development Center

Aeronautical Foundation Institute，Naval Aviation University

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