FIELD: engines and pumps.
SUBSTANCE: invention relates to diagnostics of technical state of control systems of aircraft gas turbine engines. Method of safe operation of aircraft gas turbine engine includes comparison of actual parameters of technical condition of engine structure during operation with its maximum allowable value and subsequent determination of residual life of structural elements of engine based on comparison results. As parameter selected level of operability of elements of engine structure taking into account external factors, and time until failure is determined from rate of change of performance level.
EFFECT: timely detection of pre-failure state of gas turbine engine for its maintenance.
4 cl, 4 dwg
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