Surface Characterizations of Fretting Fatigue Damage in Aluminum Alloy 7075-T6 Clamped Joints: The Beneficial Role of Ni-P Coatings.

Reza Oskouei,Raafat Ibrahim,Mohammad Barati

doi:10.3390/ma9030141

Abstract

This paper aims to characterize the surface damage as a consequence of fretting fatigue in aluminum alloy 7075-T6 plates in double-lap bolted joints through XRD, surface profilometry, and SEM analyses. The main focus was on the surface roughness and chemical phase composition of the damaged zone along with the identification of fretting fatigue crack initiations over the surface of the material. The surface roughness of the fretted zone was found to increase when the joint was clamped with a higher tightening torque and tested under the same cyclic loading. Additionally, MgZn2 (η/ή) precipitates and ZnO phase were found to form onto the surface of uncoated aluminum plate in the fretted and worn zones. The formation of the ZnO phase was understood to be a result of frictional heat induced between the surface of contacting uncoated Al 7075-T6 plates during cyclic loading and exposure to the air. The beneficial role of electroless nickel-phosphorous (Ni–P) coatings in minimizing the fretting damage and thus improving the fretting fatigue life of the aluminum plates was also studied. The results showed that the surface roughness decreased by approximately 40% after applying Ni–P coatings to the Al 7075-T6 plates.

Highlights

Mechanical and/or structural elements, which are clamped together and withstand small-amplitude oscillatory motions, may face an early failure as a result of fretting fatigue [1]
It is noted that the presence of Ni–P coatings may decrease the frictional forces acting between the washers and connecting plates
Wear and fretting fatigue damage to Al 7075-T6 plates in a double-lap bolted joint clamped with two tightening torques of 5 Nm and 8 Nm were characterized

Summary

Introduction

Mechanical and/or structural elements, which are clamped together and withstand small-amplitude oscillatory motions, may face an early failure as a result of fretting fatigue [1]. This phenomenon is very important, in aerospace structures. Fastened joints have been found as a common situation where fretting fatigue can occur, resulting in a significant reduction in fatigue life when subjected to cyclic loads [3,4]. Benhamena et al [10] reported significant reductions in the fretting fatigue life of a single-lap bolted joint composed of aluminum alloy and steel plates as a result of increasing the tightening torque. Energy dispersive spectroscopy (EDS) analyses showed a reduction in the amount of aluminum element and an increase in the amount of iron and silicon onto the damaged surface, the mechanism of this chemical

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