直通式封严篦齿内部流动和换热的实验研究

DESIGN OF EXPERIMENT PLATFORM AND INVESTIGATION OF FLOW FIELD AND HEAT TRANSFER IN STRAIGHT LABYRINTH SEAL

为了研究外界因素对高推动比航空发动机中密封装置性能的影响，介绍了在吸气式内流传热风洞实验台测量了不同雷诺数和不同齿顶厚和齿隙比的工况下对篦齿腔内部流动的影响规律， 并利用该实验台对篦齿顶板表面的换热特性进行了研究． 测量结果说明了在篦齿腔中旋涡的分布及雷诺数变化对旋涡分布的影响．

Labyrinth seals are widely used as sealing elements in aeroengine.To satisfy the imperative need of leakage and heat transfer characteristics of labyrinth seal in aeroengine, we built a big scale inhale labyrinth heat transfer wind tunnel. We made the detailed investigation of two dimensional flow field in the cavity of labyrinth seals. Detailed experimental results on the flow field reveal the two dimensional velocity and vortiex distributions in the cavity of labyrinth seal and local heat transfer coefficient distribution on the roof of labyrinths. Analyzing the results obtained at different Reynolds numbers and T/C , we found the influence on the velocity and pressure distribution in cavity of labyrinth and the influence of different Reynolds numbers and T/C on the heat transfer coefficient on the roof of labyrinth seal.