一种新的轴流压气机叶片参数化方法  

A novel parameterization method of axial compressor blade

作　　者：彭铖 李强 杨金广 刘艳 张敏[1] PENG Cheng;LI Qiang;YANG Jin-guang;LIU Yan;ZHANG Min(School of Energy and Power,Dalian University of Technology,Dalian 116024,China;China Petroleum Pipeline Engineering Co.,Ltd.,Beijing 100007,China)

机构地区：[1]大连理工大学能源与动力学院,辽宁大连116024 [2]中石油管道有限责任公司,北京100007

出　　处：《燃气涡轮试验与研究》2020年第2期34-38,62,共6页Gas Turbine Experiment and Research

基　　金：国家自然科学基金青年基金(51606026)。

摘　　要：提出一种新的轴流压气机叶片参数化设计方法。通盘考虑了轴流压气机不同设计阶段所面临的几何需求,探讨了压气机叶片的参数化准则。引入了叶片几何三要素(特征、几何和参数),并阐述了各要素之间的关系以及彼此间的转化。最后通过实例验证了所提出方法的使用效果。结果表明,这种新的叶片参数化方法可适用于不同进口马赫数的压气机叶型设计,且具有简便、鲁棒和准确的特点。A new parameterization method of axial compressor blade was proposed.Based on the geometric requirements during different phases of axial compressor design,a blade parameterization rule was conclud⁃ed firstly.Then feature,geometry and parameters,three key components of parameterization were introduced and relationship as well as transformation among them were illustrated.Finally examples are provided to demonstrate the effectiveness of the developed method.The results show that this novel method can be ap⁃plied to design compressor blade of different inlet Mach number,and it is convenient,robust and accurate.

关 键 词：航空发动机 轴流压气机 叶片设计 叶型优化 参数化 逆向设计 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]