| 摘要 |
The invention relates to a method of starting a turboengine for an aircraft, said turboengine comprising a combustion chamber, a compressor shaft on which is mounted a compressor wheel for feeding compressed air to said combustion chamber, at least one starter linked to said shaft in such a way as to provide it with the starting torque of determined value sufficient to drive it in rotation. The method comprises a step (E1) of acceleration of the compressor shaft during a first starting phase, then a step (E2) of stabilizing the speed of rotation of the compressor shaft during a second starting phase. During the acceleration step (E1), the speed of rotation of the shaft is regulated in such a way that the acceleration of the shaft remains substantially constant. |
