METHOD OF OPERATING AIRCRAFT GAS TURBINE ENGINE BASED ON ITS TECHNICAL STATE Russian patent published in 2024 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the field of operation and diagnostics of aircraft gas turbine engines taking into account specific operating conditions. Method of operating an aircraft gas turbine engine by its technical state includes recording of parameters that determine the operation of the engine, determination of the accumulated damageability of each main part (MP) of the engine, taking into account the engine operation modes and the subsequent determination of the residual life of the engine by comparing the integral length of the crack, developing in one or more dangerous places of the highest concentration of voltages of the MP, with the maximum permissible value. At that, the integral length of the crack is determined taking into account the increment of the crack length for each flight, actual engine loading cycles during operation and pre-determined calculated dependence of stress intensity factor (SIF) on crack length. Ranges of flight conditions for implementation of engine loading cycles are preliminary determined, ranges of flight conditions for implementation of loading cycles are divided into zones, for each zone and each MP, determining the calculated dependence of the stress intensity factor on the length of the crack, further, taking into account the loading cycles implementation probabilities, the weighted average dependences of the oil recovery factor on the crack length for each dangerous point of each MP of each cycle type are determined, and when determining the crack growth per flight and the integral length of the crack, the recorded parameters determining the operation of the engine are taken into account.

EFFECT: reduced cost of engine life cycle and increased accuracy of fracture length calculation.

4 cl, 3 dwg