沿流向放样的轴流压气机叶道设计方法  

Design Method of Blade Passage for Axial Compressor by Lofting along Flow Directio

作　　者：赵奕博 李浩 琚亚平[1] 张楚华[1,3] ZHAO Yibo;LI Hao;JU Yaping;ZHANG Chuhua(School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China;School of Mechanical and Power Engineering,Shanghai Jiao Tong University,Shanghai 200240,China;State Key Laboratory for Strength and Vibration of Mechanical Structures,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西安交通大学能源与动力工程学院,西安710049 [2]上海交通大学机械与动力工程学院,上海200240 [3]西安交通大学机械结构强度与振动国家重点实验室,西安710049

出　　处：《西安交通大学学报》2023年第4期39-48,共10页Journal of Xi'an Jiaotong University

基　　金：国家重大科技专项资助项目(J2019-Ⅱ-0017-0038,2017-Ⅱ-0006-0020);机械结构强度与振动国家重点实验室资助项目(SV2021-ZZ-23)。

摘　　要：针对高负荷压气机角区流动质量差、流动损失显著的问题,以NASA Rotor37为研究对象,提出了一种轴流压气机叶道几何定义与参数化建模新方法,实现了叶片、角区和端壁结构的协同设计及叶片到端壁的高阶光滑过渡,在此基础上,开展了前缘边条和叶身融合对压气机转子气动性能和内部流场影响的数值研究。结果表明,针对NASA Rotor37流道,采用该叶道设计方法对压气机转子角区改型后:绝热效率提高了0.3%,喘振裕度由11.85%增加至18.8%;下凹端壁可以帮助稳定压气机转子通流能力并减少改型过程的流量漂移;叶身融合结构在叶根处提供径向向上的压力梯度,将低能流体从叶片角区吹向主流区以减少角区流动损失,而近叶根处主流区流动损失略有增加。研究成果对发展轴流压气机先进设计方法应具有参考价值。Aiming at the problems of poor flow quality and significant flow loss at corner region of axial compressors,NASA Rotor37 axial compressor was taken as the research object to propose a new geometry definition and parameterization method for the blade passage of axial compressor,which enabled the cooperative design of blade,corner and endwall structure,and realized the high order smooth transition between blade and endwall.On this basis,the influence on the aerodynamic performance and internal flow field of hub fillet were studied.The results showed that after modifying the blade passage of NASA Rotor37,the compressor adiabatic efficiency increased by 0.3% at the design point,and surge margin increased from 11.85% to 18.8%.The concave on endwall can help stabilize the compressor flow capacity and avoid flow drift during modification.The blended blade and endwall structure can produce a transverse pressure difference,removing the low energy fluid from the corner region to the main flow to reduce corner flow separation,while the main flow losses slightly increased.The new geometry defining and parametric modeling method of the axial compressor proposed in this paper and the findings of flow improvement mechanism of the corner flow have reference value for the further development of axial compressor design system.

关 键 词：轴流压气机 角区流动 非对称端壁 前缘边条 叶身融合 

分 类 号：TK05[动力工程及工程热物理]