Rotating parts are the most loaded ones of jet engines. Geometry optimization of blade joint has to be performed in order to decrease stress and displacement. In the paper optimization methodology of compressor's blade dovetail joint was presented. Strength analysis was performed on model dovetail joint using finite element method and Ansys software. Influence of selected geometrical parameters on stress and displacement of the joint was discussed.

The article concerns the issues of the scope of optimization of the gas turbine jet engine. These issues include limiting the weight and number of engine parts. One way to reduce the weight and number of components, including the compressor assembly, is to use the BLISK's replacement construction. The replacement construction should meet the strength requirement and the vibration spectrum as well. The paper presents a comparative analysis of the influence of rotational speed on the characters and the vibration frequency of the single rotor stage of the high pressure compressor. The analysis was carried out for two different design solutions of the blade-disk connection: the classical and integral. The comparative analysis focused on three important from the point of view of operation, the engine operating ranges: work on the ground (idle) and work during take-off and climb the aircraft.

In this paper, an assessment of strength properties of the existing blade-disc dovetail joint was presented, taking the parametric optimization of its geometry. A sensitivity of the analysis was carried out to determine the relationship between the selected geometric parameters and strength properties of the structure questioned. The results from experiments and computer simulations were compared. In addition, the fatigue life of the structure was analyzed for different materials and using the change of speed ranges and parameterization of geometry.

During the operation, rotating parts of aircraft turbine engines are exposed on different types of damage. These damages mostly ensure from the difficult work conditions of this components. The article presents examples of failure of aircraft engines resulting from damage to the compressor elements. The influence of exemplary damages in the area of the blade on the work of contact surfaces in the disk rim part and the blade footer was analyzed. The distribution of stresses and pressures was determined on assuming different ranges of rotational speed as well. Numerical analyzes were performed using the ANSYS software.

Presented is the strength analysis of three variants of the compressor’s jet engine blade joint whose final geometry was created using the ANSYS optimization module. Parameterization of the blade foot and rim geometry has been introduced and a comparative analysis of the selected geometry in terms of strength has been performed. In addition, results from the experimental analysis of the substitute models of blade joint with using the digital image correlation system were presented.