METHOD OF OPERATING AIRCRAFT GAS TURBINE ENGINE ACCORDING TO ITS TECHNICAL STATE Russian patent published in 2012 - IPC G01M15/14 

FIELD: engines and pumps.

SUBSTANCE: proposed method is performed by determining engine residual operating life in comparing accumulated damageability with tolerable magnitude. Engine part damageability is described by length of fracture developing in the zone of maximum strain concentration in engine operation caused by defect not revealed in flaw detection procedure. In defining the amount of damageability, increment of fracture length is calculated in a flight and its integral length accumulated in flight with due allowance for actual straining cycles and pre-calculated design dependence of strain intensity factor on fracture length. In defining residual life, when calculated fracture length approximated to tolerance, fracture availability and length are controlled by flaw detection means to terminate operation is actual fracture length reaches its tolerance.

EFFECT: efficient and low-cost method.

2 cl, 4 dwg