跨声速离心压气机叶尖区旋涡流动特征  

Vortex flows in the blade tip region of a transonic centrifugal compressor

作　　者：郭宫达[1] 张扬军[1] 郑新前[1] 徐建中[2] 诸葛伟林[1] 

机构地区：[1]清华大学汽车安全与节能国家重点实验室,北京100084 [2]中国科学院工程热物理研究所,北京100080

出　　处：《清华大学学报（自然科学版）》2008年第11期1980-1984,共5页Journal of Tsinghua University(Science and Technology)

基　　金：中国博士后基金资助项目(20060400088);重点实验室基金项目(9140C3301020601)

摘　　要：车用增压器高压比的发展趋势,使得跨声速离心压气机叶尖区流动对气动性能影响更为重要。采用三维CFD方法,研究了跨声速离心压气机叶尖区流动对性能的影响。结果表明:额定、近失速和堵塞工况的激波呈现多样性;额定和近失速工况主叶片前缘发出的泄漏涡与相邻主叶片压力面相撞分裂成两支,堵塞工况主叶片的泄漏涡出现在压力面侧;3种工况分流叶片泄漏涡与主叶片的泄漏涡均在同一通道流出叶轮;1/2主叶片弦长之后,3工况的分离旋涡与通道涡的尺度和分布特征基本相同,叶片吸力面与机匣相交的角区形成高损失核心区。对激波结构和旋涡特征的分析有助于认识叶轮内损失分布规律和产生损失的机理。The blade tip region clearance flow is important in centrifugal compressors, especially for the high charging ratio, transonic centrifugal compressors used in vehicles. The effects of the blade tip region flow on the performance of a high charging ratio transonic centrifugal compressor were analyzed using three-dimensional CFD analyses that showed the shock waves at the design, near surge, and choke points. At the design and near surge points, the leakage vortex from the full blade leading edge collides with the neighboring full blade pressure surface and splits into two parts while at the choke point, a full blade leakage vortex appears on the pressure surface. At different operating points, splitter blade vortices and full blade vortices flow out in the same blade passage, with the separated vortex and passage vortex dimensions and distribution characteristics being similar and with high losses in the corner region between the blade suction surface and the shroud.

关 键 词：增压器 跨声速离心压气机 叶尖间隙 泄漏涡 

分 类 号：TK413.5[动力工程及工程热物理—动力机械及工程]