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In this paper, finite element stress analysis of a micro aero-engine turbine disk with different rotational forces is performed by applying Solidworks and Abaqus. Maximum safe speed of aero-engine is calculated and verificated according to the finite element analysis results. Then maximum stresses in different speeds can be calculated. Natural mode of turbine disk-blade system which is constrained by connecting hole is analyzed, and the first six order inherent frequencies and modal shapes are obtained. Stress analysis provides a theoretical basis for aero-engine speed control, design and optimization of turbine disk. The inherent mode lays the foundation for aero-engine transient analysis, spectral analysis and dynamic analysis.

Finite Element Analysis of Stress and Natural Mode for Micro Aero-engine Turbine Disk