基于CST方法的吸附式压气机叶型及抽吸方案耦合优化设计  

Coupling Optimization Design for Aspirated Compressor Airfoil and Aspirated Scheme Based on CST Method

作　　者：李俊[1] 刘波[1] 杨小东[1] 那振喆[1] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072

出　　处：《推进技术》2015年第1期9-16,共8页Journal of Propulsion Technology

基　　金：国家自然科学基金重点资助项目(51236006);先进航空发动机协同创新中心资助

摘　　要：为了探索吸附式叶型设计特点,研究了一种将类别形状函数变换法(CST)方法和人工蜂群算法相结合,利用2D程序作为流场求解器,对吸附式叶型和抽吸方案进行耦合优化设计的新型吸附式压气机叶型设计方法,并且详细论证了CST方法用于吸附式叶型优化设计的可行性。研究结果表明:耦合优化设计之后在保证叶型强度未下降的基础上总压损失降低了65%,气流转折角增加了3°,气动性能得到较大的提升。针对所优化的进口高亚声速的吸附式叶型,通过适当改变叶型前缘处的型面,可以较好地控制气流马赫数,避免产生激波,从而防止附面层厚度增加,降低叶型损失。In order to explore the design characteristics of the aspirated airfoil,a new optimization design method which combines artificial bee colony algorithm with Class-Shape-Transformation （CST） method is pre-sented. The MISES code is chosen as the flow field solver. And the feasibility of the CST method applied to aspi-rated airfoil optimization is demonstrated in detail. Research results show that the coupling optimized design can make the total pressure loss reduction by 65%,and the turning angle increases by 3° based on ensuring strength. And the aerodynamic performance gets an obvious enhancement. For high subsonic aspirated airfoil optimized in this paper,changing the airfoil surface near the leading edge appropriately can control the Mach number,and avoid forming shock. This can prevent the increasing of the boundary layer thickness, and decrease the airfoil loss.

关 键 词：吸附式压气机 耦合优化设计 人工蜂群算法 

分 类 号：V233.2[航空宇航科学与技术—航空宇航推进理论与工程]