Fretting damage is a major cause of defect. It is mandatory to study fretting in order to improve material performances, especially for titanium alloys used in aeronautics. Fretting induces wear, cracking or both damages in bodies in contact. The usual topics of fretting studies deal with one of these damages. In the one presented here, wear and cracking are studied simultaneously. This point of view allows a global approach of the blade-disk contact behavior in case of fretting in a turbojet high pressure compressor. Due to industrial constraints, the temperature of this study is 450°C and the contact geometry is coated plane on plane. This study is performed on an original experimental setup made for it. This setup enables fretting-fatigue tests at constant fretting force even if fatigue force varies. The first's results regard tribological behavior. A significant effect of pressure is shown: the more the pressure, the smaller the coating friction coefficient. The given hypothesis is an expulsion of solid lubricant contained in surface treatment. Wear results show a sacrificial behavior of the coating. The surface treatment is worn preferentially than counter-body. From an industrial point of view, this characteristic is a good way to protect the uncoated counter-body (disk) instead of coated part (blade). In parallel, another study shows effect of frequency and load variation during cycle in a more fundamental case. Wear scar profile and wear rate is modified by these two parameters. Plain fretting tests and fretting-fatigue tests are performed to study fretting cracking process. Fretting induced cracking on counter-body is modified by coating on the punch. Maximal crack length is twice as short in coating condition as in uncoated condition. In fretting-fatigue, the coating is more efficient in high cycle fatigue. As a conclusion, a polar diagram is used in order to present global results and performances of the coating.
