FIELD: engine building.
SUBSTANCE: invention relates to a combustion chamber of a gas turbine engine. A method for the determination of the ignition of a combustion chamber of a gas turbine engine contains stages, at which: first measurement (MT1) of an exhaust gas temperature behind combustion chamber (3) is obtained (E11) before attempting to ignite mentioned combustion chamber (3), temperature threshold (ST) is obtained (E12), secondary determination criterion (CS) is obtained (E13), obtained temperature threshold (ST) is updated (E14) depending on obtained secondary determination criterion (CS), second measurement (MT2) of an exhaust gas temperature is obtained (E15) after attempting to ignite combustion chamber (3), updated temperature threshold (ST) and the difference between first (MT1) and second (MT2) measurements of an exhaust gas temperature are compared (E16), and the ignition state of combustion chamber (3) is determined (E17), corresponding to a successful or unsuccessful ignition attempt, depending on the result of comparison stage (E16).
EFFECT: invention makes it possible to detect the ignition of a combustion chamber of a gas turbine engine in case of a restart of the gas turbine engine on the ground or in flight.
10 cl, 6 dwg
