Method and a device for adjusting a setpoint value of a parameter that influences thrust from a gas turbine engine

1. A method of adjusting a setpoint value of at least one parameter that has an influence on thrust of a gas turbine engine propelling an aircraft during a stage of flight of the aircraft, the method comprising:

obtaining a current value of at least one operating variable of the engine;

extracting from a pre-established table a decrement value for the at least one parameter associated with the current value of the at least one operating variable of the engine; and

adjusting the setpoint value of the at least one parameter by applying thereto the decrement value extracted from the table.

2. A method according to claim 1 , wherein the at least one operating variable of the engine is selected from:

a temperature at an inlet to the engine; and

an atmospheric pressure at the inlet to the engine.

3. A method according to claim 1 , wherein the engine is a turbojet and the at least one parameter is selected from:

a speed of rotation of a compressor of the turbojet;

a surge margin of the compressor; and

a richness of a combustion mixture of the turbojet.

4. A method according to claim 3 , wherein, during the adjustment, the setpoint value of the speed of rotation of the compressor and the setpoint value of the surge margin are adjusted.

5. A method according to claim 1 , wherein the decrement value extracted from the table for each parameter also depends on a current speed and/or a load of the aircraft.

6. A method according to claim 1 , wherein the stage of flight is a stage of the aircraft taking off and the decrement value extracted from the table for each parameter also depends on a length of a runway used by the aircraft during the takeoff stage.

7. A method according to claim 1 , wherein during the adjustment, the value of the decrement applied to the setpoint value is weighted by a weighting factor of less than 1.

8. A method according to claim 7 , wherein the weighting factor depends on a state of advance of the flight stage.

9. A non-transitory computer readable medium including a computer program including instructions for executing the method according to claim 1 when the program is executed by a computer.

10. Use, for regulating a thrust of a gas turbine engine propelling an aircraft during a stage of flight, of a setpoint value for at least one parameter that influences the thrust that has been adjusted according to the method of claim 1 .