An investigation of high and room temperature fretting fatigue of DD6-FGH96 dovetail joint in aero-engine: Experimental and numerical analysis

Experimental study and fretting fatigue life prediction in dovetail assembly considering stress–temperature nonlinear coupling effect

“…Likewise, a multiaxis high cycle fretting fatigue crack initiation life prediction model was established based on the influence mechanism of size and gradient effect in the work of Araújo et al 16 Also, Rangel et al 17 proposed a fretting fatigue life calculation method considering multiaxial non-proportional characteristics and stress gradient effect with the experimental verification of the cylindrical flat structure of aluminum alloy 7075-T651. Equally, Zhang et al 18 raised a numerical method for calculating multiaxial fatigue parameters and gradient of dovetail assembly combined with DD6-FGH96 at room temperature and 600 C. For the dovetail assembly composed of DD6-FGH96 materials at 600 C, Sun et al 19 obtained that the comprehensive effect of fretting wear and crystal slip is the main cause of fretting fatigue failure. In addition, Bhatti et al 20,21 analyzed the fretting fatigue behavior of fretting fatigue specimens composed of aluminum 2024-T351 and Ti-6Al-4V under in-phase and out-of-phase loads by using the finite element method and damage mechanics method.…”

Experimental and computational investigation of fretting fatigue characterized by nominal contact pressure in dovetail structures

“…The stress concentrations and uncertain manufacturing tolerances make the test results cannot be related to other structures. [8][9][10][11][40][41][42][43][44][45][46][47][48] Moreover, a fretting model based on a sophisticated constitutive model and damage evolution equations is too time consuming and not efficient enough for engineering design. In the turbine industry, fretting fatigue was assessed based on a simple estimate of the contact pressure over yield stress of the material.…”

“…The structural experiments should reconstruct failure processes in the real structures under similar loading conditions but suffered from complex stress distributions in the specimens and on contact surfaces. The stress concentrations and uncertain manufacturing tolerances make the test results cannot be related to other structures 8‐11,40‐48 . Moreover, a fretting model based on a sophisticated constitutive model and damage evolution equations is too time consuming and not efficient enough for engineering design.…”