METHOD OF OPERATING AN AIRCRAFT GAS TURBINE ENGINE BASED ON ITS TECHNICAL STATE Russian patent published in 2019 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: invention relates to diagnostics of technical state of aircraft gas turbine engines taking into account specific operating conditions. Achievement of maximum allowable values of accumulated damage of the main parts when using the declared method occurs after a longer period of operation compared to the prototype. Thus, using the disclosed method reduces the cost of the engine life cycle. In the disclosed method of operating an aircraft gas turbine engine based on its technical state, consisting in comparing the actual engine running time and the accumulated damage of the main engine components with their maximum permissible values determined from the results of resource tests on the ground test bench, and subsequent determination of residual life of engine and its main parts based on results of said comparison, wherein accumulated damage of engine main parts is determined as sum of products of number of standard loading cycles assigned for flight, determined by ranges of cyclic loading variation of main engine parts, in its turn determined by characteristic parameters of engine operation, to corresponding single damageability, first of all range of operation of aircraft gas turbine engine in coordinates of full temperature T*_in and total pressure P*_in at engine inlet is divided into zones, determining for each main part and each typical loading cycle maximum unit damageability in each zone, then during flight parameter values T*_in and P*_in, upon completion of flight to determine accumulated damage of each main part using single defectiveness, corresponding to selected zone by parameters T*_in and P*_in peak of each selected loading cycle, if the peak of the selected cycle corresponds to the boundary of the zones, then to determine the accumulated damage of each main part, there used is unit damageability belonging to one of the adjacent zones, in which its value will be the least, besides, the number and sizes of zones are selected for each main part individually.

EFFECT: more complete use of potential capabilities of main engine parts by resource due to application of improved mechanism for calculation of accumulated damage.

1 cl, 4 dwg, 1 tbl