| 摘要 |
A regulator device (10) for regulating a turbine engine (3). The regulator device (10) includes mechanical power take-off means (100) for taking off power mechanically from a gas generator (4), and an engine computer (20) controlling said engine (3) to comply with at least a first limitation (LimTET, LimT45) of a temperature (TET, T45) of the gas within the engine, and with a second limitation (LimNg) of a speed of rotation (Ng) of the gas generator (4). The engine computer (20) determines whether the speed of rotation (Ng) of the gas generator has reached said second limitation (LimNg), and whether said temperature (TET, T45) has reached said first limitation (LimTET, LimT45). An avionics computer (30) causes the mechanical power take-off means (100) to operate if the speed of rotation (Ng) of the gas generator (4) has reached said second limitation (LimNg), and if said temperature (TET, T45) has not reached said first limitation (LimTET, LimT45). |
| 主权项 |
1. A method of regulating an aircraft power plant including at least one turbine engine, the turbine engine including a gas generator, an auxiliary shaft, and a turbine assembly, the turbine assembly including a free turbine and a high-pressure turbine arranged upstream from the free turbine, the gas generator including a compressor connected to the high-pressure turbine, the power plant further including mechanical power take-off means connected to the gas generator via the auxiliary shaft for taking off power mechanically from the gas generator and the power plant further including an engine computer, the method comprising:
the engine computer controlling the turbine engine so as to comply with at least a first limitation (LimTET, LimT45) for a temperature (TET, T45) of the gas within the turbine assembly, and with a second limitation (LimNg) for a speed of rotation (Ng) of the gas generator; during an evaluation step (STP1), determining whether the speed of rotation (Ng) of the gas generator has reached the second limitation (LimNg); during the evaluation step (STP1), determining whether the temperature (TET, T45) of the gas within the turbine assembly has reached the first limitation (LimTET, LimT45); and during an optimization step (STP2), if the speed of rotation (Ng) of the gas generator has reached the second limitation (LimNg) and if the temperature (TET, T45) of the gas within the turbine assembly has not reached the first limitation (LimTET, LimT45), then the engine computer controlling the mechanical power take-off means to increase the amount of power taken off mechanically from the gas generator and thereby reduce the speed of rotation (Ng) of the gas generator so as to optimize a power developed by the turbine engine. |
