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The paper presents the key stages of developing a geometric model of the axial compressor blade. The model is based on Bezier curves, which are used to design the parts of airfoil and allow making local changes to the airfoil and blade geometry. This model is designed to assess the technical condition of the axial compressor being a part of an industrial gas turbine or gas-turbine units, depending on the defects of axial compressor blade row (in the gas-flow channel) and the turbine as a whole. As a part of the study the algorithm, which describes the process of the blade formation, were presented. Although the study presents the main equations of the model based on the key geometric parameters of the airfoil, provides examples of airfoil, blade and stage modelling using the presented method, and shows the results of model verification using numerical simulation methods.

Mathematical model of the axial compressor blade in system assessing technical condition of the industrial gas turbine