Labyrinth seal systems are used in aeroengines to seal the clearance, the understanding of the wear mechanism of labyrinth seal system is necessary to achieve better sealing performance. In this work a series of tests are conducted on a high-speed test rig capable of fin tip speeds of 100 m/s. With force and temperature measurements recorded in each case, the influence of specimen geometry is investigated. Surface examination and debris analysis is also performed using microscopy post-test. The wear mechanism was found to be influenced by fin geometry. A discrete fin was observed to trigger a more efficient material removal mechanism at both incursion conditions. Where the fin segment and ring-shaped fin leading to increased temperatures and material smearing. The heat dissipate role of fin was also observed during test where longer contact time of fin and abradable gives better heat removal performance.

迷宫密封系统用于航空发动机密封间隙，了解迷宫密封系统的磨损机理对于获得更好的密封性能是必要的。在这项工作中，一系列测试是在能够达到 100 m/s 的鳍尖速度的高速试验台上进行的。通过在每种情况下记录的力和温度测量值，研究试样几何形状的影响。表面检查和碎片分析也使用显微镜后测试进行。发现磨损机制受翅片几何形状的影响。观察到离散翅片在两种侵入条件下都会触发更有效的材料去除机制。其中翅片段和环形翅片导致温度升高和材料涂抹。