<p>The paper presents numerical studies of how mistuning of the natural vibration frequency of a single blade – taken as the most dangerous mistuning scenario – affects the stress-strain state of critical zones of the disk of a low-pressure axial compressor of an aircraft gas turbine engine. A 2% mistuning of the blade’s natural frequency was achieved by reducing its airfoil height. Finite-element (FE) models of the bladed wheel were developed considering centrifugal and harmonic power loading and contact interaction in a dovetail-type root joint. The numerical model was verified by comparing computed results with experimental data. It was determined that thickening the disk rim reduces the maximum equivalent stresses. The influence of different excitation harmonics on the disk’s vibro-stress level was investigated, and mistuning was considered. It is shown that the blades’ bending-torsional and torsional vibration modes have the strongest influence on increasing the vibro-stress in the disk’s critical points, especially when excited by the 1st and 19th harmonics of the power loading. It was found that the largest relative increase of stresses in the disk’s critical points occurs for the 5th harmonic of loading, which is associated with the interference of the natural modes of the blade–disk system.</p>