Abstract
Induced fatigue has led to a large number of deviations of service failures in a wide range of applications, where the deterioration of properties occurs due to the slipping between surfaces at a small displacement. In this article, a numerical simulation of a semi-elliptical crack in the dovetail joint of the compressor was performed to understand the destruction of the blade due to the stress contour in the contact area. A three-dimensional crack is modelled using the ANSYS Finite Element Analysis program, and the blade profile is modelled by CATIA V5R20 software. The study considers a model of an open semi-elliptical crack, and the parameters of the movement of the crack tip are estimated using three-dimensional singular elements of the crack tip in ANSYS. Initially, a three-dimensional finite element model of a compressor blade with a dovetail contact area was simulated in CATIA V5 and analysed in the ANSYS working environment to determine the maximum principal stresses in the crack-free region. After the crack front has been precisely identified and confirmed, fracture modelling is used to determine the impact of crack size with one side, as well as rotation speed, on fracture parameters (stress intensity factors).
Highlights
The root of the dovetail of the compressor blades is the case when the induced fatigue failure is a fairly common occurrence
Results and discussions the results obtained from carrying out non-linear static analysis on 3-Dimensional dovetail joint of compressor are presented. 4.1Analysis of Compressor Blade dovetail joint without Crack In Fig.7. and Fig.8.show both the von-mises stress and the maximum principal stress at the contact region, which gives the identification of crack location at the contact region of the dovetail joint
4.2 Analysis of Compressor Blade dovetail joint with Crack Based on the results of the 3D analysis, high stressed location near the blade and disc contact region which is the probable location of initiation of crack was identified
Summary
The root of the dovetail of the compressor blades is the case when the induced fatigue failure is a fairly common occurrence. Under the influence of centrifugal loading and vibration, fatigue occurs between the root of the blade, the disk and the stresses in the vicinity of the contact, which must be accurately estimated to predict the fatigue life. P. Papanikos et al conducted a three-dimensional nonlinear analysis by the finite element method of this area of the dovetail in the disk assemblies of the aircraft engine compressor using contact elements. Nonlinear finite element analysis was used to determine the stress state of the disk / blade assembly under various rotation conditions.[8-10]
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