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为揭示尾迹/势流干扰下压气机静叶附面层的非定常流动机理,采用数值方法对单级高负荷跨声速风扇中径处的非定常流场进行模拟,针对尾迹/势流干扰下的静叶附面层非定常流动特征进行研究。基于尾迹/势流与叶片附面层干扰模型,通过叶片壁面摩擦力、近壁面附面层湍动能和壁面静压脉动,详细分析了尾迹和势流干扰下尾迹对高负荷静叶附面层流动状态的影响。研究发现:在非定常条件下,尾迹干扰能够“刺穿”静叶附面层,使得静叶附面层发生跨越转捩现象。尾迹和受其诱导的势流碰撞静叶前缘产生的压力扰动波在压力面附面层内以声速传播,影响压力面整个弦长的静压和摩擦力分布,而在吸力面上,扰动波的传播仅局限在前缘区域部分弦长上,吸力面和压力面传播现象不同与逆压梯度和曲面凸、凹形状相关。
In order to reveal the unsteady flow mechanism of compressor stator vane laminates under wake / potential disturbances, a numerical method is used to simulate the unsteady flow field at the mid-diameter of a single-stage high-load transonic fan. The static laminar unsteady flow characteristics are studied. Based on the wake / potential flow and blade interference model, the effects of wake and potential flow wake on the high-load static blade attachment layer were analyzed in detail by the friction force of blade wall surface, the turbulent kinetic energy of the near- Influence of flow status. The study found that under unsteady conditions, wake interference can “pierce ” static leaf attachment layer, making the static leaf laminar stratification occurred transition phenomenon. Wake and induced potential flow collision pressure generated by the front edge of the vortex wave in the pressure surface within the surface layer at the speed of sound propagation, affecting the pressure surface of the entire chord length of the static pressure and friction distribution, and in the suction surface, the disturbance The propagation of wave is confined to only part of the chord of the leading edge region. The difference of the propagating phenomenon between the suction surface and the pressure surface is related to the reverse pressure gradient and convex and concave shapes.