FIELD: engines and pumps.
SUBSTANCE: invention relates to method and system for starting a gas turbine engine of an aircraft. Gas turbine engine comprises a combustion chamber, a compressor shaft on which a compressor wheel is mounted to supply compressed air to said combustion chamber, at least one starter connected to said shaft in such a manner as to impart to it a torque for starting a certain value to drive it into rotation. Method comprises step (E1) of accelerating compressor shaft during the first start phase, then step (E2) of stabilizing the rotation speed of the compressor shaft during the second start phase. During acceleration stage (E1), the shaft rotation speed is adjusted so that the acceleration of the shaft remains substantially constant.
EFFECT: invention allows to increase efficiency of launching a gas turbine engine of an aircraft.
9 cl, 4 dwg
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