低负荷和高负荷压气机叶栅气动性能的实验和数值模拟  

Experiment and numerical simulation on aerodynamic performance of low-loaded and highly-loaded compressor cascades

作　　者：原泽 郑群[1] 岳国强[1] 董静涛 姜玉廷[1] YUAN Ze;ZH ENG Qun;YUE Guoqiang;DONG Jingtao;JIANG Yuting(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,China;Institute of Systems Engineering,Academy of Military Sciences,the Chinese People’s Liberation Army,Beijing 100074,China)

机构地区：[1]哈尔滨工程大学动力与能源工程学院,哈尔滨150001 [2]中国人民解放军军事科学院系统工程研究院,北京100074

出　　处：《航空动力学报》2021年第4期724-733,共10页Journal of Aerospace Power

基　　金：国家科技重大专项(2017-Ⅰ-0011-0012,2017-Ⅰ-0009-0010)。

摘　　要：为了明确采用高负荷设计及一般设计(低负荷)方法的压气机气动性能和流动转捩的差异,进行了不同攻角下的叶栅吸力面流谱绘制和参数测量实验。并基于实验边界条件,采用γ-θ转捩模型开展数值研究。结果表明:与低负荷叶栅相比,随着攻角的增大,高负荷叶栅主流附面层由附着流变为分离流,尾迹的宽度和损失强度增加,并与角区分离融合为一个"带状"损失区。而低负荷叶栅的角区分离仍为紧贴壁面的开式分离,主流附面层仍然附着在壁面上。结果表明:高负荷设计增强了叶栅内逆压力梯度,这使得流动更容易分离,表现为表面形状因子呈现大范围的"峰谷"型分布,转捩模式也由局部旁路转捩变为全叶高范围的分离泡转捩。To clarify the difference in aerodynamic performance and flow transition between compressors using highly-loaded design and general design(low-loaded), the cascade experiments including suction side flow pattern and parameter measurement were performed. Based on the experimental boundary conditions, numerical researches on the suction boundary layer with γ-θ transition model were also conducted. Result showed that, compared with the low-loaded cascade, as the incidence angle increased, the flow boundary layer in highly-loaded cascade transformed from the attached flow to the separated flow, which enhanced wake width and loss and made wake integrate with corner separation loss region into a "strip-shape" loss region. Meanwhile, the flow boundary flow in low-loaded cascade was still an attached flow and the corner separation maintained open separation close to the endwall. The results indicated that highly-loaded design enhanced the inverse pressure gradient in the cascade, causing the flow more easily separated, the surface shape parameter presented a wide range of "peak" distribution, and the transition mode also changed from local bypass transition to all-span separation-induced transition.

关 键 词：低负荷和高负荷叶型 压气机叶栅实验 气动性能 转捩 攻角 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]