旋转冲压压缩转子激波/附面层/泄漏流干扰研究  

Numerical Research of Shock Wave/Boundary Layer/Leakage Flow Interaction in the Ram-rotor

作　　者：管健[1] 韩吉昂[1] 钟兢军[1] 苑辰光 

机构地区：[1]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5期950-956,共7页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51406022);国家自然科学基金重点项目(No.51436002);辽宁省自然科学基金资助项目(No.2013020129);辽宁省教育厅科学研究一般项目(No.L2013199);辽宁省高等学校创新团队支持计划资助项目(No.LT2015004)

摘　　要：为分析附面层和泄漏流对旋转冲压压缩转子内激波结构的影响,开展了旋转冲压压缩转子内部流场的数值研究,并从激波形成与变化的角度分析激波与附面层,激波与泄漏流的相互作用。研究表明,S_2流面激波与轮毂附面层、S_1流面激波与隔板尾缘低速分离流体团相互作用能够改变激波的结构形态、作用位置,压比升高时低速团的影响范围增大。S_1流面激波在泄漏涡的作用位置处发生偏折,与无间隙时相比,有间隙时旋转冲压压缩转子在喉部及以后流道内更易形成激波串。In order to investigate the influence of boundary layer and tip leakage flow on the shock wave structure, the flow field in the ram-rotor was researched numerically. The interaction between shock wave and boundary layer, together with the interaction between shock wave and leakage flow, was analyzed in terms of the formation and variation of shock waves. It has been found that the structure and position of shock waves can be changed, respectively, due to the interaction between shock waves in S2 stream surface and boundary layer of the hub wall and the interaction between shock waves in S1 stream surface and low momentum separation flow near the strake trailing edge. As total pressure ratio rises, the low momentum zone is also extended. Shock waves in S1 stream surface are bent at the position of leakage vortex. Compared with the ram-rotor without tip clearance, the shock train is more easily formed in the throat and later flow passage of the ram-rotor with the tip clearance.

关 键 词：旋转冲压压缩转子 激波 附面层 泄漏流 数值研究 

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]