Patent ID: 11905893
Assignee: SAFRAN HELICOPTER ENGINES
Field: Transport (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 0:
1. A method for regulating a non-propulsion electrical generation turbomachine configured to supply electrically a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to an energy distribution module by at least one supply bus, the turbomachine supplying each supply bus via the energy distribution module according to a supply rate, the turbomachine comprising a high-pressure shaft and having a high-pressure rotation speed N1, and a low-pressure shaft, having a low-pressure rotation speed N2, the regulation method comprising:
a step of determining the power requirement of each propulsion rotor,
a step of determining the power requirement of each supply bus as a function of the power requirement of each propulsion rotor,
a step of determining the elementary power requirement of each supply bus as a function of the supply rate and the power requirement of each supply bus,
a step of determining the overall power requirement from all of the elementary power requirements of the supply buses,
a step of determining an anticipation parameter from the overall power requirement,
a step of determining a high-pressure rotation speed set point from a low-pressure rotation speed set point and from a measurement of the low-pressure rotation speed of the turbomachine and of said anticipation parameter, and
a step of determining a fuel flow rate set point of the turbomachine from the high-pressure rotation speed set point and from a measurement of the high-pressure rotation speed.