Abstract
This paper aimed to solve the impact of operational abrasive wear on the rotor blades of the axial compressor of the turboshaft engine on the decrease in its total compression efficiency ηCt and its transition into unstable work mode (surge). This process is analyzed based on the obtained data by operating TV3-117 helicopter turboshaft engines in high dust atmosphere conditions. Abrasive wear of the rotor blades of axial compressors causes mechanical damage to the blades, reducing their strength, changing their geometry, and aerodynamic properties, reducing the life of the whole compressor and thus the entire engine. Destruction of the compressor of a turboshaft engine may occur suddenly as a result of unstable compressor operation caused by damaged axial compressor blades due to their damage by the abrasive effect of dust.
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