Method and a device for generating a command for the flow rate of fuel that is to be injected into a combustion chamber of a turbine engine

1. A method of generating a fuel meter command for a fuel meter to control a fuel flow rate to be injected into a combustion chamber of a turbine engine for propelling an aircraft, comprising:

during a stage of starting the turbine engine:

open-loop generating of an open-loop fuel flow rate command from a pre-established relationship; and

concurrently with the open-loop generating, closed-loop monitoring of at least one operating parameter of the turbine engine selected from:

a rate of acceleration of a compressor of the turbine engine; and

a temperature at an outlet from a turbine of the turbine engine;

the closed-loop monitoring comprising:

generating, using at least one corrector network associated with the at least one operating parameter, a respective correction signal for correcting the open-loop fuel flow rate command; and

selectively correcting the open-loop fuel flow rate command to obtain a corrected open-loop fuel flow rate command using the respective correction signal of one of the at least one corrector network when correction is required in order to maintain the at least one operating parameter in a respective determined range of values,

wherein the at least one corrector network has a respective gain value that depends on a static pressure in the combustion chamber and on a total pressure at an inlet of a fan of the turbine engine; and

wherein the fuel meter command is generated as the open-loop fuel flow rate command when the open-loop fuel flow rate command is not corrected during the closed-loop monitoring and the fuel meter command is generated as the corrected open-loop fuel flow rate command when the open-loop fuel flow rate command is corrected using the respective correction signal during the closed-loop monitoring.

2. The method according to claim 1 , wherein, during the closed-loop monitoring, the rate of acceleration of the compressor of the turbine engine is maintained in the respective determined range of values between a minimum acceleration setpoint value and a maximum acceleration setpoint value.

3. The method according to claim 1 , wherein, during the closed-loop monitoring, the temperature at the outlet from the turbine of the turbine engine is maintained in the respective determined range of values below a maximum temperature setpoint value.

4. The method according to claim 1 , wherein the at least one corrector network generating the respective correction signal comprises:

a first corrector network generating a respective first correction signal associated with the rate of acceleration of the compressor, and

a second corrector network generating a respective second correction signal associated with the temperature at the outlet from the turbine;

wherein the closed-loop monitoring further includes selecting one of the first correction signal or the second correction signal, the selected correction signal being used for the selective correcting of the open-loop fuel flow rate command.

5. The method according to claim 4 , wherein the selected correction signal is the second correction signal generated by the second corrector network associated with the temperature at the outlet from the turbine.

6. The method according to claim 4 , wherein each of the first corrector network and the second corrector network is of the proportional integral or proportional double integral type, and wherein the first correction signal or the second correction signal is evaluated from a difference between a current value of the at least one operating parameter with which it is associated and a respective determined setpoint value.

7. The method according to claim 1 , further including saturating the fuel meter command after the selective correcting.

8. The method according to claim 7 , wherein said saturating comprises forcing the fuel meter command to take one or the other of a first limit value and a second limit value corresponding respectively to a minimum percentage and to a maximum percentage of the open-loop fuel flow rate command that is not yet selectively corrected, if the current value of the fuel meter command is respectively less than the first limit value or greater than the second limit value.

9. The method of claim 1 , wherein the turbine engine is an aircraft turbine engine.

10. The method of claim 1 , wherein the turbine engine is a two-spool turbine engine.

11. The method of claim 10 , wherein the compressor is a high-pressure compressor of the two-spool turbine engine.

12. A device for generating a fuel meter command for a fuel meter to control a fuel flow rate to be injected into a combustion chamber of a turbine engine for propelling an aircraft, comprising:

a processor; and

a non-transitory computer readable medium storing instructions that, when executed by the processor, configure the processor, during a state of starting the turbine engine, to:

open-loop generate an open-loop fuel flow rate command from a pre-established relationship; and

concurrently with the open-loop generation, closed-loop monitor at least one operating parameter of the turbine engine selected from:

rate of acceleration of a compressor of the turbine engine; and

temperature at an outlet from a turbine of the turbine engine;

wherein to monitor the at least one operating parameter, the processor is configured to:

generate, using at least one corrector network associated with the at least one operating parameter, a respective correction signal for correcting the open-loop fuel flow rate command, and

selectively correct the open-loop fuel flow rate command to obtain a corrected open-loop fuel flow rate command using the respective correction signal of one of the at least one corrector network when correction is required in order to maintain the at least one operating parameter in a determined range of values,

wherein the at least one corrector network has a gain value that depends on a static pressure in the combustion chamber and on a total pressure at an inlet of a fan of the turbine engine, and

wherein the fuel meter command is generated as the open-loop fuel flow rate command when the open-loop fuel flow rate command is not corrected during the closed-loop monitoring and the fuel meter command is generated as the corrected open-loop fuel flow rate command when the open-loop fuel flow rate command is corrected using the respective correction signal during the closed-loop monitoring.

13. The device according to claim 12 , wherein the at least one corrector network comprises a plurality of corrector networks sharing a common integrator.

14. The device according to claim 13 , wherein the common integrator is saturated.

15. The device according to claim 12 , wherein the at least one corrector network generating the respective correction signal comprises a plurality of corrector networks generating respective correction signals, the processor configured to select the respective corrective signal delivered by one of the plurality of corrector networks to correct the open-loop fuel flow rate command.

16. A turbine engine including a device according to claim 12 .

17. A method of generating a fuel meter command for a fuel meter to control a fuel flow rate to be injected into a combustion chamber of an aircraft turbine engine for propelling an aircraft, comprising:

during a stage of starting the aircraft turbine engine:

open-loop generating of an open-loop fuel flow rate command from a pre-established relationship; and

concurrently with the open-loop generating, closed-loop monitoring of at least one operating parameter of the aircraft, turbine engine selected from:

a rate of acceleration of a compressor of the aircraft turbine engine; and

a temperature at an outlet from a turbine of the aircraft turbine engine;

the closed-loop monitoring comprising:

generating, using at least one corrector network associated with the at least one operating parameter, a respective correction signal for correcting the open-loop fuel flow rate command; and

selectively correcting, the open-loop fuel flow rate command to obtain a corrected open-loop fuel flow rate command using the respective correction signal of one of the at least one corrector network when required in order to maintain the at least one operating parameter in respective determined range of values;

wherein the at least one corrector network has a respective gain value that depends on a static pressure in the combustion chamber and on a total pressure at an inlet of a fan of the turbine engine; and

wherein the fuel meter command is generated as the open-loop fuel flow rate command when the open-loop fuel flow rate command is not corrected during the closed-loop monitoring and the fuel meter command is generated as the corrected open-loop fuel flow rate command when the open-loop fuel flow rate command is corrected using the respective correction signal during the closed-loop monitoring.

18. The method of claim 17 , wherein the turbine engine is a two-spool turbine engine and the compressor is a high-pressure compressor of the two-spool turbine engine.