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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 development trend of high-pressure ratio of vehicle turbocharger makes the influence of the transonic compressor flow on the aerodynamic performance more important. A three-dimensional CFD method was used to study the influence of flow on the transonic centrifugal compressor tip area. The results show that the shock waves at rated, near stalling and jamming conditions are diversified. The leakage vortices from the leading edge of the main blade at rated and near stall conditions collide with the pressure surface of the adjacent main blade to split into two branches, The leakage vortex of the vane appears on the pressure surface side. The leaking vortex of the split vane in three conditions and the leaking vortex of the main vane all flow out of the impeller in the same channel. After the chord of the main vane 1/2, the separation vortex and channel vortex The scale and distribution characteristics are basically the same, and the corner area where the suction surface of the blade intersects with the casing forms a core area of high loss. The analysis of shock structure and vortex characteristics helps to understand the law of loss distribution and the mechanism of loss generation in impeller.