Thermal barrier coating interface cracking prediction method

Abstract

The invention relates to a thermal barrier coating interface cracking prediction method. The method comprises the following steps: S1, constructing a two-dimensional geometric model of the thermal barrier coating; s2, dividing grids, and inserting cohesion units in TGO / TC and TGO / BC interfaces; s3, setting parameters of the TC layer, the TGO layer, the BC layer and the SUB layer respectively, and adding damage parameters to TGO / TC and TGO / BC interface cohesion units; s4, assembling the two-dimensional geometric model of the thermal barrier coating, and setting the thermal cycle load time of the viscosity analysis step as T; s5, applying a symmetric boundary condition to the left side of the thermal barrier coating two-dimensional geometric model, applying a periodic boundary condition MPC multi-point coupling constraint condition to the right side of the thermal barrier coating two-dimensional geometric model, and constraining the y-direction freedom degree at the bottom; s6, applying a thermal cycle load of the analysis step through a self-defined amplitude curve; and S7, circulating the step S6 to complete a preset number of thermal load cycles to obtain a cracking prediction result of the two-dimensional geometric model of the thermal barrier coating. The method can effectively predict the nucleation position and the expansion condition of the interface crack of the thermal barrier coating.

Description

technical field [0001] The invention relates to the field of thermal barrier coatings, in particular to a method for predicting interface cracking of thermal barrier coatings. Background technique [0002] Gas turbines are an important pillar of the modern aviation industry and a symbol of the country's major equipment manufacturing level. Thermal barrier coating technology is one of the core technologies for the development of advanced heavy-duty gas turbines. It covers the surface of the turbine substrate with a layer of thermal insulation material with low thermal conductivity and high stability. It not only has a thermal barrier effect, but also prevents oxidation and corrosion. And damage to the blade caused by foreign matter erosion. At present, the gas temperature of F-class heavy-duty gas turbines has reached 1400°C, and the gas temperature of heavy-duty gas turbines will exceed 1700°C in the future. Under the extremely high temperature working environment, the fai...

AI Technical Summary

Problems solved by technology

Under the extremely high temperature working environment, the failure and damage of the thermal barrier coating is exacerbated, which greatly shortens the safe service life of the gas turbine. Therefore, it is of great significance to study the failure mechanism of the thermal barrier coating to improve the safety of the gas turbine.

Images