摘要
综述空气动力学理论中激波-边界层相互影响的一般特性以及静压气体轴承中的激波与边界层相互影响理论与试验研究。指出随着计算技术和微流体测试技术的发展,气膜内的压力分布、速度分布和马赫数分布,根据流场各段不同的流动特点,将可以采用合适的湍流模型进行计算机模拟,并采用相关试验得到验证。静压气体轴承中的激波-边界层相互影响将得到更深入的研究,必将促进对较高供气压力和较大气膜间隙条件下,静压气体轴承气膜入口、出口转角区和气膜内轴承特性的全面了解。
The research work on interaction of shock wave with boundary layer in aerodynamics is reviewed, including its general characteristics, theoretical and experimental researches on interaction of shock wave with boundary layer in externally pressurized gas bearings. With the developments of CFD and micro-fluid testing technology, the pressure distribution, velocity distribution, Mach number distribution in the clearance can be simulated by computer with proper turbulence models according to the flow feature in the separate parts of fluid field, and experimentally tested. A deeper research of the theory on interaction of shock wave with boundary layer in externally pressurized gas bearings will be conducted, and further comprehension of its bearing performance of the inlet region, outlet corner region and bearing feature in the clearance will be advanced.
出处
《机械工程学报》
EI
CAS
CSCD
北大核心
2006年第9期1-5,共5页
Journal of Mechanical Engineering
基金
国家自然科学基金资助项目(50335010)
关键词
气体轴承
激波
边界层
Gas beating Shock wave Boundary layer
