Diagnostic model of helicopter turboshaft engine

The article presents a qualitative assessment of the impact on the engine components characteristics of the malfunction occurrence in the flow part of the aviation gas turbine engines, which lead to changes in its geometry. Using the example of a compressor, it is shown that when defects appear in it, two of its characteristics are deformed: efficiency and pressure characteristics (which is confirmed by a significant number of studies). It is concluded that in order to reliably diagnose aviation gas turbine engines by thermogasodynamic parameters, the mathematical model must take into account the change in two characteristics for each engine component of the flow part (and not only the change in the characteristics of the efficiency of the nodes). A linear mathematical model of a helicopter turboshaft turbine engine is presented and the results of calculating the influence coefficient for a given control law are presented. The peculiarity of the presented model is that the state of each engine component is characterized by two state parameters: for compressors, this is the head characteristic and the efficiency characteristic, for turbines, performance characteristics and efficiency.