Damage evolution by using the near-tip fields of a crack in gas turbine liners

A residual lifetime prediction study has been performed on a combustion liner metallic material exposed to elevated temperatures by simulating the evolution of plastic work fields at a crack tip under monotonically loading. The strain and stress distribution has been computed by finite element analysis. The method gives a measure of the metal degradation and enables to evaluate the failure limit of a progressive damage under the operating conditions of gas turbine components. The study allows making a correlation between the progress of damage of a combustion liner and the loading conditions, the material type and the geometry of a specimen by the parametric design construction.