FIELD: aviation industry. SUBSTANCE: invention relates to aircraft engines. Proposed method of recording fuel ignition in afterburner of gas turbine engine includes measurement of gas pressure in afterburner. According to proposed method time derivative of measured parameter logarithm is determined and if its value exceeds adjusted operation threshold, signal is generated to ignite fuel. Control computer provides determination of time derivative of measured parameter logarithm and compares its value with adjusted operation threshold. Use of proposed method provides reliable recording of fuel ignition in afterburner, cuts down fuel delivery on fire-up site and reduces negative action onto turbine blades and gas dynamic stability of compressor at afterburner selection. EFFECT: improved reliability in operation. 2 cl, 1 dwg
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