Patent ID: 9404425
Filing Date: 2016-08-02
CPC Classification: F02C,F05D

Claim Text:
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 (STP during the evaluation step (STP during an optimization step (STP