轴流压气机超音叶片新设计技术研究  

An Investigation on a New Technique for Designing Supersonic Blade Airfoil of Axial Flow Compressor

作　　者：肖敏[1] 刘波[2] 程荣辉[3] 

机构地区：[1]中国燃气涡轮研究院3室,四川江油621703 [2]西北工业大学航空动力与热力工程系,陕西西安710072 [3]中国燃气涡轮研究院压气机室,四川新都610500

出　　处：《航空动力学报》2002年第1期83-86,共4页Journal of Aerospace Power

摘　　要：介绍了一种轴流压气机超音叶片新设计技术 ,即叶型中弧线用任意多段圆弧生成 ,前缘用椭圆弧连接。该方法可以灵活控制叶型中弧线的曲率分布 ,有效控制扩散因子 ,提高气流抗分离的能力。椭圆形的前缘可减弱超音气流在前缘进口区的加速程度 ,降低进口弓形波的强度 ;叶型入口段理想的曲率分布可以合理组织进口激波结构和位置 ,大幅降低激波损失。This paper presents a new technique for designing the superso nic blade airfoil of axial flow compressor,whose meanline consists of multi circular and leading arc is elliptic.This new method makes the design flexible to control the curvature distribution of meanline,effective to control the diffusion factor of designed blade,and it enhances flow to resist separation.The ellipse arc may depress the acceleration of supersonic flow in inlet area,decrease the strength of inlet shock wave.The ideal curvature in front part of designed blade may reasonably form shock position,so the shock loss is reduced greatly.Two kinds of airfoil are modified by means of this new method.Flow fields of cascade are calculated by the finite volume TDM method.The results show this new technique is an excellent application to engineering.

关 键 词：轴流压气机 超音叶片 中弧线曲率 椭圆弧 激波损失 设计技术 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]