Contact Mechanics and Material Removal in Abradable Linings

耐磨性衬里用于压缩机和涡轮机，因为它们允许最大限度地减少叶尖间隙，同时不会遭受叶尖磨损的惩罚。他们对航空发动机特别感兴趣，因为它们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。这一建议是关于调查切削型磨损经历的可磨耗衬里，在一个刀片尖端进入衬里。以前的研究认为这一过程类似于高速加工，而最近从发动机试验中观察到的结果表明，碎片实际上是从触头后部喷射出来的。在本研究中，将开发一个模拟航空发动机压气机摩擦的演示平台，并使用超声技术结合有限元模型研究相关的接触力学。通过这种方法，将确定材料的失效点，并深入了解为什么碎片会从接触器的后部喷出。叶尖的几何形状也将作为研究的一部分，以及它们对材料去除的影响。航空发动机制造商希望进一步减少叶片尖端间隙，以提高发动机效率，从而增加磨损事件的频率，因此这个主题领域尤其相关。

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.