Thermo-mechanical Coupling of Turbine Disk and Fatigue Crack Growth of Central Hole

Based on the finite element software ABAQUS/Franc3D, the stress and fatigue crack growth of an Aero-Engine Turbine Disk were investigated. Firstly, grid-independent verification was performed to ensure calculation accuracy. Secondly, the thermal conductivity of the turbine disk was simulated to determine the temperature distribution. Then, the stress-strain calculation and static strength checking were carried out under the condition of coupled thermal-mechanical loads. Finally, the fatigue crack growth parameters and fatigue crack growth life at the center hole were calculated. The results show that the static strength of the turbine disk meets the requirements at the maximum rotational speed, and the central hole area is the dangerous point of stress concentration. The temperature change rate at the crack tip increased with the depth of the crack, which leads to the disturbance of the stress field at the crack tip, and the crack changes from mode I to mode I/II. The fatigue crack growth life prediction results are dangerous, but it can provide a basis for damage tolerance design of turbine disk.