Abstract
This study is concerned with analysis of fatigue crack growth and life-time prediction for aviation GTE compressor disk under operation conditions. For consideration were different combinations of rotational speed, temperature, surface flaw form and sizes as well as elastic-plastic titanium alloy BT3-1 properties are employed. A crack growth rate equation is derived involving the fracture process zone size and nonlinear stress intensity factor. The assessments of the structural integrity of the rotating disk are compared for elastic and elastic-plastic solutions. It is stated that the traditional elastic crack growth models overestimate the residual fatigue lifetime with respect to the nonlinear fracture mechanics approach.
Highlights
Today civil aviation gas turbine engine (GTE) components design becomes very demanding due to high temperatures, complex mechanical loads, corrosive environment and long expected lifetimes
It was found that the plastic fracture process zone sizes and In-factor were strong functions of the material constitutive equations, crack size, specimen configuration, and loading conditions, which were reproduced from nonlinear stress intensity factors (SIF)
Predicting the crack growth rate of the aviation GTE compressor disk according to the nonlinear fracture mechanics approach was much faster and the residual fatigue lifetime was lower compared with elastic modeling, thereby demonstrating that the low cycle fatigue material properties significantly affected the damage accumulation and growth in the fracture process zone ahead of the crack tip
Summary
Today civil aviation GTE components design becomes very demanding due to high temperatures, complex mechanical loads, corrosive environment and long expected lifetimes Such loading conditions lead to fatigue crack initiations and their propagation up to reaching a critical zone in rotating disks. Most of the critical zones are characterized by the presence of plastic deformations in which the effective stresses exceed the yield strength of the material at the corresponding temperature These circumstances assume the application of nonlinear fracture and continuum damage mechanics approaches to aviation GTE components lifetime prediction. It was found that the plastic fracture process zone sizes and In-factor were strong functions of the material constitutive equations, crack size, specimen configuration, and loading conditions, which were reproduced from nonlinear SIFs. The present work provide an appropriate numerical study to part-through surface cracks lifetime predictions for rotating components of civil aviation gas-turbine engines. For consideration were different combinations of rotational speed, temperature, surface flaw form and sizes as well as elastic-plastic titanium alloy BT3-1 properties are employed
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