Abstract
The aim of the work is to improve the quality with a decrease in the complexity of diagnosing an axial compressor
 of a helicopter gas turbine engine with erosive-abrasive wear of its blades. Regularities of changes in the structural
 and diagnostic parameters of the compressor depending on the operating time and the region of operation of the engine
 are revealed. The values of the main gas-dynamic parameters and the wear of the compressor blades and the links
 between them, which determine the limiting state of the TV3-117 type helicopter gas turbine engine, are substantiated.
 A method for determining the residual life of the compressor is proposed, taking into account the region of operation
 of the helicopter. The quality of compressor diagnostics was assessed using the gas-dynamic parameters of a helicopter
 gas turbine engine in operation.
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