# US 11,905,893 B2 · Method and system for regulating a non-propulsion electrical generation turbomachine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,905,893 B2 - Document ID: US11905893B2 - Status: Granted - Kind: B2 - Application number: 17/442,029 - Filed: 2020-03-20 - Published: 2022-06-09 - Granted: 2024-02-20 - Earliest claimed: 2019-04-01 - Assignees: Safran Helicopter Engines - Applicants: Safran Helicopter Engines - Inventors: Stéphane Meyer Beddok; Vincent Poumarede - Web page: https://patentgrep.com/patent/US11905893B2 ## CPC - F02C 9/26: Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232) - B64D 27/33: Hybrid electric aircraft - B64D 31/18: for hybrid-electric power plants - B64D 41/00: Power installations for auxiliary purposes - F02C 3/10: with another turbine driving an output shaft but not driving the compressor - B64D 2221/00: Electric power distribution systems onboard aircraft - F05D 2220/76: an electrical generator - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement. ## Claims ### Claim 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. ### Claim 2 (depends on 1) The method for regulating according to claim 1, wherein the energy distribution module is configured to supply each supply bus by the turbomachine and by a battery. ### Claim 3 (depends on 1) The method for regulating according to claim 1, wherein the power requirement of a propulsion rotor is determined as a function of at least one of the following parameters of said propulsion rotor: the thrust, the rotation speed and the pitch of said propulsion rotor. ### Claim 4 (depends on 1) The method for regulating according to claim 1, wherein at least two propulsion rotors are electrically connected to the energy distribution module by the same supply bus. ### Claim 5 (depends on 4) The method for regulating according to claim 4, wherein, the supply bus supplying at least two propulsion rotors as a function of predetermined sharing rates, the method comprises a step of determining the elementary power requirement of said supply bus as a function of the power requirement of each propulsion rotor connected to said supply bus, the predetermined sharing rates and the supply rate of said supply bus. ### Claim 6 (depends on 1) The method for regulating according to claim 1, wherein the anticipation parameter is determined from a database receiving in input the overall power requirement. ### Claim 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. ### Claim 8 (depends on 7) A non-propulsion electrical generation turbomachine configured to supply electrically a plurality of propulsion rotors of an aircraft, 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 turbomachine comprising the system for regulating according to claim 7. ### Claim 9 (depends on 8) An aircraft comprising a plurality of propulsion rotors, at least one energy distribution module, at least one supply bus connecting each propulsion rotor to the energy distribution module, the turbomachine according to claim 8 supplying each supply bus via the energy distribution module according to a supply rate.