超声速低反力度压气机动叶激波结构的研究

The Study of Shock-wave Structure of a Supersonic Low-reaction Compressor Blades

为研究叶栅通道内的激波结构,以某3级高负荷低反力度压气机首级超声速级动叶为研究对象。采用数值模拟方法考察了不同工况下激波与叶片吸力面分离流动、激波与叶顶泄漏流动之间的相互干扰情况。结果表明:流场中的激波是诱发吸力面边界层分离的一个重要因素。此外,叶顶泄漏流动会在叶顶附近对流道中激波产生影响,导致激波的变形乃至断裂。

In order to explore the shock -wave structure, taking the rotor of an supersonic first stage of three- stage highly -loaded low -reaction axial compressor as research objection. The shock -wave structure and its interference with blade suction surface separation flow and with tip leakage flow were investigated under different working conditions by numerical simulations. The resuhs shows that the shock - wave in the flow field is an important factor for the separation of the boundary layer on the suction surface. And the tip leakage flow can be influenced by the shock -wave, which leads to the deformation and even fracture of the shock -wave.