Method for quickly stopping the rotor of a helicopter after landing
A method for quickly stopping the propulsion rotor of a helicopter after landing, comprising, following a request for quickly stopping the engine by a helicopter pilot, the following steps managed by the control unit of the turbomachine: Detecting the absence of the thermal stabilization phase of the gas generator of at least one turbomachine, controlling an extinction of the combustion chamber of the gas generator of at least one turbomachine, maintaining the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least one electrical machine to ventilate the gas generator and stopping the main rotor of the helicopter by means of a mechanical brake.
1. A method for quickly stopping a main rotor of a helicopter after landing, the helicopter comprising:
the main rotor for propulsion of the helicopter;
at least one turbomachine;
a main gearbox connected between said at least one turbomachine and the main rotor;
a turbomachine control unit;
an electric power supply network; and
at least one electrical machine coupled to the electrical power supply network, said at least one turbomachine including:
a gas generator equipped with a mechanical shaft;
a free turbine coupled to the main rotor via the main gearbox and mechanically independent of the mechanical shaft of the gas generator; and
a system configured to mechanically couple the at least one electrical machine to the gas generator,
wherein the method comprises, following a step of requesting a quick stop of the at least one turbomachine by a helicopter pilot, causing an extinction of a combustion chamber of the gas generator of the at least one turbomachine, the following steps managed by the turbomachine control unit of the at least one turbomachine:
detecting an absence of a thermal stabilization phase of the gas generator of the at least one turbomachine to confirm that the step of requesting the quick stop of the at least one turbomachine is a request for quickly stopping the main rotor,
in the event of absence of the thermal stabilization phase, maintaining the rotation of the gas generator of which the combustion chamber is extinguished, by means of said at least one electrical machine mechanically coupled to the gas generator and powered by the electrical power supply network, to ventilate the gas generator, and
stopping the main rotor of the helicopter by means of a brake.
2. The method according to claim 1 , wherein the maintaining of the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least electrical machine is maintained for a predefined ventilation period starting the combustion chamber is extinguished, and a power supply of the at least one electrical machine is stopped at the end of the predefined ventilation period.
3. The method according to claim 1 , wherein the maintaining of the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least electrical machine is maintained as long as at least one measured temperature of the gas generator is greater than a first threshold and/or an absolute value of a measured temperature gradient is greater than a second threshold, or a power supply of the at least one electrical machine is stopped.
4. The method according to claim 1 , wherein the at least one turbomachine comprises at least two turbomachines each turbomachine of the at least two turbomachines having a respective free turbine connected to the main rotor via the main gearbox, wherein the step of requesting the quick stop of the at least one turbomachine comprises requesting the quick stop of the at least two turbomachines, and wherein the turbomachine control unit is the turbomachine control unit of the at least two turbomachines, and the method also comprises, prior to the step of requesting the quick stop of the at least two turbomachines, a step of requesting operation in auxiliary power unit mode of at least one turbomachine of the at least two turbomachines driving the following steps managed by the turbomachine control unit of the at least two turbomachines:
increasing a torque of at least one turbomachine of the at least two turbomachines until at least one other turbomachine of the at least two turbomachines supplies a zero torque to the main gearbox,
disengaging said at least one turbomachine supplying a zero torque resulting in said at least one turbomachine supplying a zero torque being disengaged, and
operating in auxiliary power unit mode said at least one turbomachine having been disengaged to drive the at least one electrical machine and supply power to the electrical power supply network of the helicopter,
the step of requesting the quick stop of the at least two turbomachines by the helicopter pilot causing the extinction of the combustion chamber of the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox, and the step of detecting the absence of the thermal stabilization phase being applied to the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox.
5. The method according to claim 4 , wherein the step of requesting operation in auxiliary power unit mode of at least one turbomachine of the at least two turbomachines is requested by the helicopter pilot prior to the step of requesting the quick stop of the of the at least two turbomachines, and information on the actual operation in auxiliary power unit mode of at least one turbomachine is transmitted to the helicopter pilot prior to the step of requesting the quick stop of the of the at least two turbomachines.
6. The method according to claim 1 , wherein the electrical power supply network of the helicopter is configured to be power supplied by at least one alternator driven by an auxiliary power unit.
7. The method according to claim 1 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
8. The method according to claim 2 , wherein the maintaining of the rotation of the gas generator of which the combustion chamber is extinguished by means of said at least electrical machine is maintained as long as at least one measured temperature of the gas generator is greater than a first threshold and/or an absolute value of a measured temperature gradient is greater than a second threshold, or the power supply of the at least one electrical machine is stopped.
9. The method according to claim 2 , wherein the at least one turbomachine comprises at least two turbomachines each turbomachine of the at least two turbomachines having a respective free turbine connected to the main rotor via the main gearbox, wherein the step of requesting the quick stop of the at least one turbomachine comprises requesting the quick stop of the at least two turbomachines, and wherein the turbomachine control unit is the turbomachine control unit of the at least two turbomachines, and the method also comprises, prior to the step of requesting the quick stop of the at least two turbomachines, a step of requesting operation in auxiliary power unit mode of at least one turbomachine of the at least two turbomachines driving the following steps managed by the turbomachine control unit of the at least two turbomachines:
increasing the torque of at least one turbomachine of the at least two turbomachines until at least one other turbomachine of the at least two turbomachines supplies a zero torque to the main gearbox,
disengaging said at least one turbomachine of the at least two turbomachines supplying a zero torque resulting in said at least one turbomachine supplying a zero torque being disengaged, and
operating in auxiliary power unit mode said at least one turbomachine having been disengaged to drive the at least one electrical machine and supply power to the electrical power supply network of the helicopter, the step of requesting quick stop of the at least two turbomachines by the helicopter pilot causing the extinction of the combustion chamber of the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox, and the step of detecting the absence of the thermal stabilization phase being applied to the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox.
10. The method according to claim 3 , wherein the at least one turbomachine comprises at least two turbomachines each turbomachine of the at least two turbomachines having a respective free turbine connected to the main rotor via the main gearbox, wherein the step of requesting the quick stop of the at least one turbomachine comprises requesting the quick stop of the at least two turbomachines, and wherein the turbomachine control unit is the turbomachine control unit of the at least two turbomachines, and the method also comprises, prior to the step of requesting the quick stop of the at least two turbomachines, a step of requesting operation in auxiliary power unit mode of at least one turbomachine of the at least two turbomachines driving the following steps managed by the turbomachine control unit of the at least two turbomachines:
increasing a torque of at least one turbomachine of the at least two turbomachines until at least one other turbomachine of the at least two turbomachines supplies a zero torque to the main gearbox,
disengaging said at least one turbomachine supplying a zero torque resulting in said at least one turbomachine supplying a zero torque being disengaged, and
operating in auxiliary power unit mode said at least one turbomachine having been disengaged to drive the at least one electrical machine and supply power to the electrical power supply network of the helicopter,
the step of requesting quick stop of the quick stop of the at least two turbomachines by the helicopter pilot causing the extinction of the combustion chamber of the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox, and the step of detecting the absence of the thermal stabilization phase being applied to the gas generator of each turbomachine of the at least two turbomachines still engaged to the main gearbox.
11. The method according to claim 2 , wherein the electrical power supply network of the helicopter is configured to be power supplied by at least one alternator driven by an auxiliary power unit.
12. The method according to claim 3 , wherein the electrical power supply network of the helicopter is configured to be power supplied by at least one alternator driven by an auxiliary power unit.
13. The method according to claim 4 , wherein the electrical power supply network of the helicopter is configured to be power supplied by at least one alternator driven by an auxiliary power unit.
14. The method according to claim 5 , wherein the electrical power supply network of the helicopter is configured to be power supplied by at least one alternator driven by an auxiliary power unit.
15. The method according to claim 2 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
16. The method according to claim 3 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
17. The method according to claim 4 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
18. The method according to claim 5 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
19. The method according to claim 6 , wherein the electrical power supply network of the helicopter comprises at least one battery of the electrical power supply network powering said at least one electrical machine.
20. The method according to claim 9 , wherein the step of requesting operation in auxiliary power unit mode of at least one turbomachine is requested by the helicopter pilot prior to the step of requesting the quick stop of the at least two turbomachines, and information on the actual operation in auxiliary power unit mode of at least one turbomachine is transmitted to the pilot prior to his request for quickly stopping the engine.