叶身/端壁融合扩压叶栅气动性能实验与数值研究  

Experimental and Numerical Investigation on the Aerodynamic Performance of a Compressor Cascade Using Blended Blade and End Wall

作　　者：伊卫林[1] 李嘉宾[2] 季路成[2] YI Wei-Lin LI Jia-Bin JI Lu-Cheng(School of Mechanical Engineering, Beijing Institute of Technology, Beijing 100081, China School of Aerospace and Engineering, Beijing Institute of Technology, Beijing 100081, China)

机构地区：[1]北京理工大学大学机械与车辆学院,北京100081 [2]北京理工大学大学宇航学院,北京100081

出　　处：《工程热物理学报》2017年第8期1655-1664,共10页Journal of Engineering Thermophysics

基　　金：国家自然科学基金面上项目(No.51476010;No.51376023)

摘　　要：已有的数值研究表明叶身/端壁融合设计能有效推迟、减弱或消除压气机角区分离,但实验数据缺乏。为了弥补这一不足,本文针对一42°折转角的NACA65扩压叶栅进行了吸力面叶身/端壁融合设计,并首次在低速平面叶栅风洞中进行了对比实验,证实了叶身/端壁融合扩压叶栅性能提升能力。基于实验结果,进一步校验了RNG-KE、SST等不同湍流模型的模拟精度,并基于SST模型结果揭示了叶身/端壁融合设计的作用机理。实验结果表明:叶身/端壁融合扩压叶栅能在设计攻角及正攻角下改进叶栅性能,提高总压损失系数7%~8%。数值结果表明:融合的加入重新组织了端区流场,避免了流体在叶栅后部吸力面角区内的过度堆积而发生的强三维分离,有效缓解了原型叶栅高损失流动。The design of blended blade and end wall had been proved to be useful in delaying, reducing, and eliminating the corner separation at the compressor. But an experience hasn＇t been made to verify the numerical study yet. In order to make up for the problem, this paper makes an experiment to verify that the design of blended blade and end wM1 can promote the aerodynamic performance through an NACA65 diffusion cascade with the turning angle 42 degrees. Based on the experiment, the numerical study was made through two different turbulence model RNG-KE, and SST. Then the details of the flow field and the effect of the blended blade and end wall design on the corner separation are discussed and analyzed through the SST results. The experiment shows that the design of blended blade and end wall can improve the performance of the cascade when the incidence angle was positive or at the design point, and the total pressure loss coefficient was reduced by 7%-8%. The numerical study shows that the design of the blended blade and end wall can have a good effect on the corner flow of the cascade. The strong 3-d corner separation caused by the stack of the flow happened at the tail end of the suction side was avoided, and the flow losses of the prototype cascade were reduced.

关 键 词：扩压叶栅 角区分离 叶身/端壁融合 风洞实验 CFD 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]