考虑加工误差及多工况影响的压气机叶型鲁棒性优化  

Robustness Optimization of Compressor Blade Profile Considering Machining Errors and Multi-Working Conditions

作　　者：杨荣菲[1] 沈法祥 龚志豪 王彬[1] YANG Rongfei;SHEN Faxiang;GONG Zhihao;WANG Bin(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing Jiangsu 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《海军航空大学学报》2024年第5期557-566,共10页Journal of Naval Aviation University

基　　金：航空科学基金(201907052001)。

摘　　要：针对压气机叶型在宽攻角宽马赫数范围内低损失工作、叶型性能对加工误差不敏感的工程需求,首先,建立了考虑加工误差及几何参数的叶型优化流程;然后,以某压气机静子叶型为研究对象,基于构建的代理模型,在设计马赫数0.87(跨音流动)与低马赫数0.7(亚音流动)下开展了考虑加工误差及多攻角工况影响的压气机叶型鲁棒性优化设计研究。结果表明:针对跨音流动工况优化获得的叶型,其设计马赫数攻角特性大幅改善,但亚音流动工况下的攻角特性略微恶化;针对亚音流动工况优化获得的叶型,其攻角特性在多个低马赫数工况下大幅改善,在跨音流动工况下恶化。To address the engineering needs of compressor blade profiles operating at low losses over a wide angle of attack and a wide range of Mach number,and the insensitivity of blade performance to machining errors,a blade profile optimization process considering machining errors and geometric parameters is established firstly.Then,based on the built-in surrogate model,a robust optimization design study of compressor blade profile is conducted for a specific compressor stator blade profile at design Mach numbers of 0.87(transonic flow)and 0.7(subsonic flow),taking into account machining errors and multi-angle-of-attack conditions.The results show that the blade profile optimized for transonic flow conditions has greatly improved angle-of-attack characteristics,but slightly deteriorated for subsonic flow conditions.The blade profile optimized for subsonic flow conditions has greatly improved angle-of-attack characteristics for multiple low Mach number conditions,but deteriorated for transonic flow conditions.

关 键 词：压气机叶型 多工况 加工误差 鲁棒性优化 气动性能 

分 类 号：TJ3[兵器科学与技术—火炮、自动武器与弹药工程]