This is a repository copy of Investigating the Application of a Honeycomb Abradable Lining in the Turbine Stage of an Aero-Engine
This is a repository copy of Investigating the Application of a Honeycomb Abradable Lining in the Turbine Stage of an Aero-Engine
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2019
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现代航空发动机采用可磨耗衬片来减少轴向气体泄漏。在高速试验机上，采用原位测试技术，结合试验后的显微镜和X射线荧光元素分析，研究了一种新型镍基高温合金蜂窝可磨耗衬层的磨损性能。特别是考虑了改变镍铝化物填料比的效果，以及试样热老化的影响。可磨耗材料的压实发生，导致翅片磨损，沿着高的力和温度。这种磨损机制是循环的，伴随着碎屑喷射和火花。可磨耗件的老化通常导致翅片磨损的增加，除了在一种情况下这导致可磨耗件的改进的断裂和翅片的改进的切割性能。高达21000 RPM的速度，这对应于200 ms-1的叶尖速度。类似地，显微镜载物台可以以0.1至2000（cid：358）ms-1之间的线速度操作。该装置由定制的Labview程序操作，并且通过以设定的速度将可磨耗样品朝向旋转盘移动直到达到规定的深度来创建侵入事件。
Modern aero-engines use abradable linings to reduce axial gas leakage. In this study the wear performance of a new developed nickel superalloy honeycomb abradableliningwas investigated on a novel high-speed test rig, using in-situ measurement techniques, combined with post-test microscopy and X-ray fluorescence based elemental analysis. In particular the effect of changing the nickel-aluminide filler ratio was considered, as well as the impact of thermal ageing of the specimens. Compaction of abradable occurs, resulting in fin wear, along with high forces and temperatures. This wear mechanism is cyclic with debris ejection and sparks. Ageing of the abradable generally leads to an increase in fin wear, with the exception that in one case this lead to improved fracture of the abradable and an improved cutting performance by the fin. up to speeds of 21000RPM, with this corresponding to a blade tip speed of 200ms -1 . Similarly, the microscope stage can operate with a linear speed between 0.1 and 2000 (cid:358) ms -1 . The rig is operated by a customized Labview programme, and an incursion event is created by moving the abradable sample towards the rotating disc at a set speed, until a prescribed depth is reached.