Contact Mechanics and Material Removal in Abradable Linings

可磨损衬里用于压缩机和涡轮机，因为它们允许将叶片尖端间隙降至最低，同时不会受到叶片尖端磨损的惩罚。他们对航空发动机特别感兴趣，因为航空发动机有助于提高发动机效率并最大限度地减少航空燃料的消耗。该建议涉及调查可磨损衬里在叶片尖端侵入衬里时所经历的切削型磨损。以前的研究认为这一过程类似于高速加工，而最近发动机试验的观察表明，实际上碎片是从触点的后部喷出的。在这项研究中，将开发一个演示平台来模拟航空发动机压缩机的摩擦，并使用超声波技术结合有限元模型来研究相关的接触机理。通过这种方法，将识别材料故障点，并深入了解为什么碎片从触点后部喷射出来。作为这项研究的一部分，还将研究叶片尖端的几何形状，以及它们对材料去除的影响。由于航空发动机制造商希望进一步将叶片尖端间隙降至最低，以提高发动机效率，从而增加磨损事件的频率，因此这一主题领域尤其相关。

Abradable linings are used within compressors and turbines as they allow blade tip clearances to be minimised, whilst not suffering the penalty of blade tip wear. They are of particular interest in aero-engines, where they help to improve engine efficiency and minimise the consumption of aviation fuel. This proposal is concerned with investigating cutting type wear experienced by abradable linings, during the incursion of a blade tip into the lining. Previous studies have considered the process to be similar to that of high speed machining, whereas recent observations from engine tests have indicated that debris is in fact ejected from the rear of the contact.In this study a demonstrator platform will be developed for simulating aero-engine compressor rubs, and the associated contact mechanics investigated using an ultrasonic technique in combination with a finite element model. Through this approach, material failure points will be identified, and insight gained as to why debris is ejected from the rear of the contact. Blade tip geometries will also be investigated as part of this study, as well as their effect on material removal. This topic area is particularly pertinent as aero-engine manufacturer's looks to minimise blade tip clearances further inorder to increase engine efficiency, thus increasing the frequency of abrasion events.