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

Claim 6:
7. A system 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, having a high-pressure rotation speed N1, and a low-pressure shaft, having a low-pressure rotation speed N2, the regulation system comprising:
a power determination module configured to determine the power requirement of each propulsion rotor,
an anticipation module configured to determine:
i. a power requirement of each supply bus as a function of the power requirement of each propulsion rotor,
ii. an elementary power requirement of each supply bus as a function of the supply rate and the power requirement of each supply bus,
iii. an overall power requirement from all of the elementary power supply requirements of the supply buses,
iv. an anticipation parameter from the overall power requirement,

a regulation module configured to determine:
i. 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
ii. 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.