Numerical simulation the finite element method (FEM) of stress and strain for the chosen coatings TBCs on turbine blades loaded with laser impulses

This paper presents the results of laser ablation the barrier coating TBCs (Al2O3, ZrO2) generated on aircraft engine turbine blade made for nickel base alloy ŻS6K-- WI. Authors used neodymium impulse Nd: YAG laser, radiation with a wavelength of 1064 nm. In parallel with the laboratory experiment was performed numerical simulation of laser ablation. FEM simulation results were used for to choose the relevant laser parameters (impulse duration, impulse shape and course in time, power density) and to identify the temperature distribution heat fluxes and the state of stress and strain in the critical zones of the barrier coating TBCs. The simulation was carried out using the finite element method program LS-Dyna. On the basis of numerical simulation shown the influence of the impact layer TBCs as a thermal insulation and shown place the appearance of destructive deformation. Defined distributed tension as a function of time and estimated time destruction parts the barrier layer during the laser ablation micromachining. Model 3D of the engine turbine blades DV - 2, Analyzed piece of blade, physical model, temperature maps, maps of the reduced stress are presented in the paper