Abstract

The axial compressor of a gas turbine engine is the main part that determines the characteristics of the engine (aerodynamic characteristics, geometry, weight, efficiency, reliability, etc.). The technological features of blades in axial compressors have a fundamental influence on the aerodynamicdynamic characteristics of engines and their reliability during operation. The strength characteristics of the compressor blade and rotor also have a basic effect on the reliability performance; then, the breakage of the compressor blade can lead to local destruction of the engine and cause disaster for the plant. Considering the operating conditions of compressor blades and their role in gas turbine engines, it is found that compressor blades are a decisive factor in the reliability and quality of engines. When the compressor blade is damaged, it is understood as a change in geometrical characteristics, weight, physical and chemical properties of the substrate and coating, etc., due to the influence during engine operation. For the outside of the blade, the leading edge of the blade is often eroded (changing the radius of the leading edge, reducing the length of the pitch); damage by foreign bodies (significant deformation of the profile); change the shape of the tips of the blades; excessive roughness of the surface of the blades. It is mainly caused by foreign objects such as dust particles in the air, contamination of the blades, and significantly increased surface roughness of the blades. Therefore, it is necessary to pay attention to the exploitation of the engine and to solve the problem of causes and rules of erosion, pitting, and roughness. The article presents the results of studying the movement rules of dust particles in the clearance of the flow path of the axial compressor and the general characteristics of erosion, the change in shape of the compressor blade and other parameters and the characteristics of the gas turbine engine. This article presents a model to calculate the basic parameters of air flow and dust particles moving in the flow path of the compressor. Simulation can be performed using the ANSYS Fluent application, thereby comparing the assessment of the actual results with those of surveys. The results presented in the envelope are the basis for studying the negative effects of operating conditions on the engine, as well as proposing effective measures to protect the compressor blade from erosion and the methods of diagnostics of gas turbine engine.