Numerical and Experimental Analysis of a High-Pressure Aviation Engine Turbine Disc

In the process of designing and developing the aviation turbine engine (ATE), certain reliability criteria based on safety, economic and strategic requirements must be ensured. Therefore, maximum attention must be paid to the methodologies of predicting and verifying the limit states and to their continuous improvement, necessitated by ever-increasing demands. An extremely strained part of the aviation engine is a high-pressure turbine disc (HPTD). While observing the science of basic relations of elasticity and strength, the analytical check of disc strength is only possible for simple disc shapes. Such tasks are currently being resolved primarily through the application of universal computer programs based on finite element method (FEM). The paper describes a numerical and experimental analysis of the HPTD disc, where the main problem is crack formation. The aim is to analyze the loads this disc is exposed to and to detect the stress concentration that is the cause of these cracks using available numerical and experimental methods.