高速高负荷压气机叶栅损失特性实验研究  

Experimental Investigation of Losses in a High-Speed High-Loading Compressor Cascade

作　　者：唐雨萌[1] 柳阳威[1,2] 陆利蓬[1,2] 陆华伟[3] TANG Yu-Meng LIU Yang-Wei LU Li-Peng LU Hua-Wei(National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics, School of Energy and Power Engineering, Beihang University, Beijing 100191, China Collaborative Innovation Center of Advanced Aero-Enginer Beijing 100191, China Marine Engineering College of Dalian Maritime University, Dalian 116026, China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]先进航空发动机协同创新中心,北京100191 [3]大连海事大学轮机工程学院,大连116026

出　　处：《工程热物理学报》2017年第8期1624-1633,共10页Journal of Engineering Thermophysics

基　　金：国家自然科学基金项目(No.51676007;No.51376001;No.51420105008)

摘　　要：实验测量了某高速高负荷压气机叶栅两个马赫数(0.5884和0.5)下-8°、-6°、-4°、-1.69°、0°、2°、4°和8°共8个攻角的栅后流场,分析了其损失特性随着攻角的变化规律。结果表明:设计马赫数0.5884下,该叶栅低总压损失系数对应的攻角范围较小,随着攻角往两端偏离最优攻角,叶栅损失很快就急剧增加;从2°到4°攻角,流场结构发生了改变,近叶中区域也开始发生了较大的分离,而近端区的角区分离反而减小,使得总压损失未迅速增加,而是基本不变;随着攻角进一步增大到8°,发展成了全叶高的大尺度分离流动,尾迹速度亏损急剧增大,总压损失也急剧增大。The flow features behind a high-speed high-loading compressor cascade was mea- sured under two Mach number conditions （0.5884 and 0.5） both at 8 incidences （-8°, -6°, -4°, -1.69°, 0°, 2°, 4° and 8°）, and the total pressure loss coefficient versus incidence angle was analyzed. It is found that the effective operating range is quite small under tile design Mach immber conditions （Ma = 0.5884）, the performance deteriorates seriously as the incidence deviates from the design condition. The flow structure changes when the incidence switches from 2° to 4°; considerable separation occurs in the mid-span region and the corner separation decreases reversely, resulting in the nearly invariable loss scale rather than speedy increasing. When the incidence increases to 8°, the corner separation no longer stokes in the endwall-caseade corner, but spreads along the spanwise as whole passage stall, with the wake velocity decay and the total pressure loss coefficient increasing dramatically.

关 键 词：高负荷 高速叶栅 压气机 攻角特性 实验研究 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]