RU2021139242A - GAS TURBINE ENGINE ACCELERATION CONTROL METHOD - Google Patents

Claims (18)

1. A method for regulating the acceleration of a gas turbine engine (1), while the gas turbine engine (1) contains a combustion chamber (5), a high-pressure turbine (6), located downstream of the combustion chamber (5) and configured to drive the shaft (8) high pressure, and a low pressure turbine (7) located downstream of the high pressure turbine (6) and configured to drive the low pressure shaft (9), characterized in that it includes the following steps: - applying (100) mechanical power to the high pressure shaft (8) until the speed of the high pressure shaft (8) reaches a predetermined value, then - selection (200) of mechanical power from the high pressure shaft (8) so as to maintain the rotation speed at a given value. 2. The method according to claim 1, wherein the step of extracting (200) mechanical power from the high pressure shaft (8) is performed by the first electric machine (11) in the electric generator mode. 3. Method according to claim 2, wherein the step of supplying mechanical power (100) to the high pressure shaft (8) is performed by the first electric machine (11) in electric motor mode. 4. The method according to one of paragraphs. 1-3, containing the following stage, performed in parallel with the stage of selection (200) of mechanical power from the shaft (8) of high pressure: supply (250) of mechanical power to the shaft (9) of low pressure. 5. The method according to any one of paragraphs. 1-4, in which the method includes the following step, performed in parallel with the step of supplying (100) mechanical power to the high pressure shaft (8): extracting (150) mechanical power from the low pressure shaft (9). 6. The method according to claim 5, comprising the following step, performed in parallel with the step of selecting (200) mechanical power from the high pressure shaft (8): ) mechanical power to the low pressure shaft (9) is performed by the second electric machine (12) in the electric motor mode, and the stage of mechanical power extraction (150) from the low pressure shaft (9) is performed by the said second electric machine (12) in the electric generator mode . 7. The method according to any one of paragraphs. 1-6, in which the gas turbine engine (1) contains a high pressure compressor (4) located upstream of the combustion chamber (5) and driven by a high pressure shaft (8), while the method includes the following step: monitoring of the high pressure compressor (4) by determining the surge parameter of the high pressure compressor (4), wherein the step of supplying (100) mechanical power to the high pressure shaft (8) is performed if the surge parameter of the high pressure compressor (4) reaches a threshold value. 8. Gas turbine engine (1) for an aircraft, containing: a high pressure turbine (6) located downstream of the combustion chamber (5) and connected to the high pressure shaft (8); a low pressure turbine (7) located downstream of the high pressure turbine (6) and connected to the low pressure shaft (9); - device (11) for supplying mechanical power to the shaft (8) of high pressure; - device (11) for the selection of mechanical power from the shaft (8) of high pressure; - a control system (13), which is connected to the supply device (11) and the mechanical power take-off device (11), while the control system (13) is configured to implement the gas turbine engine acceleration control method according to one of paragraphs. 1-7. 9. Gas turbine engine (1) according to claim 8, in which the mechanical power supply device (11) is the first electric machine (11) configured to operate in the electric motor mode, and the mechanical power take-off device (11) is the first electric machine (11), configured to operate in the mode of an electric generator. 10. Gas turbine engine (1) according to any one of paragraphs. 8 or 9, comprising a second electric machine (12) which is connected to the low pressure shaft (9) and which is configured to operate as an electric motor and supply mechanical power to the low pressure shaft (9). 11. Gas turbine engine (1) according to claim 10, in which the second electric machine (12) is configured to operate in the mode of an electric generator and take mechanical power from the low pressure shaft (9).