Abstract
Rotational components of aero engine turbine are the most important components. It operates at high temperature and under conditions of extreme environmental attack such as oxidation, corrosion and wear. These conditions can cause cracking of rotational components. The failure damage modes of turbine are classified in terms of main components as flow path parts, rotating such as rotor, groove, disk, and blade. Aero-engine turbine components such as discs and blades are susceptible to environmentally assisted cracking. Unlike fatigue crack growth, this involves crack growth under constant load. If the crack grows long enough, sudden failure can occur with catastrophic consequences. It is therefore desirable to identify the limiting crack size within fixings so that they can be inspected at regular intervals and removed from service before failure occurs. Three dimensional axis-symmetric finite element models were created to simulate a disc and the portion of a blade. The finite element method (FEM) allowed the prediction of the point of crack initiation and the crack propagation using the orientations of the maximum principal stresses. Stress intensity factor (SIF) is the base parameter in strength analysis regarding fracture mechanics. For a correct determination of SIF in this paper, combining J-integral approach and FEM is used. J-integral is a path independent integral around the crack tip.
Highlights
DURING the past four decades an extensive research of fracture mechanics has greatly enhanced the understanding of structural failure
New specifications have been established to meet the requirements of fracture mechanics, of airframes and power plant generation systems
A more stringent safety criterion, assuming a pre-existing flow in critical component, has been adopted to asses service life of aircraft. This emphasizes the significance of fracture mechanics as a tool for analysis
Summary
DURING the past four decades an extensive research of fracture mechanics has greatly enhanced the understanding of structural failure. A more stringent safety criterion, assuming a pre-existing flow in critical component, has been adopted to asses service life of aircraft This emphasizes the significance of fracture mechanics as a tool for analysis. The use of the J-integral and its critical value JC as a fracture criterion has been developed into elasticplastic and fully plastic regimes [3, 4] Various other approaches, such as resistance curve (R-curve) [5], crack tip displacement (CTOD) [5], and equivalent energy method [6] have been proposed but lack the flexible analytical basis of the J-integral procedure. For the fairly complicated geometry and loading conditions in the specimens of this study, the finite element technique is used to calculate both the temperature distribution and the stress intensity factor. The objective of the analytical work is to provide the relationship between the stress intensity factor and various mechanical and thermal load conditions. Elements of this investigation, the finite element technique is used to calculate the temperature distribution and stress intensity factor
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