# US 2022/0286019 A1 · Turbogenerator for hybrid electric aeronautical propulsion > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2022/0286019 A1 - Document ID: US20220286019A1 - Status: Published application - Kind: A1 - Application number: 17/597,786 - Filed: 2020-07-24 - Published: 2022-09-08 - Earliest claimed: 2019-07-26 - Assignees: Safran Helicopter Engines; Safran - Applicants: Safran Helicopter Engines; Safran - Inventors: Loïs Pierre Denis VIVE; Christophe Ludovic Jean-Claude VIGUIER - Web page: https://patentgrep.com/patent/US20220286019A1 ## CPC - H02K 16/00: Machines with more than one rotor or stator {(machines for transmitting mechanical power from a driving shaft to a driven shaft and comprising structurally interrelated motor and generator parts H02K51/00; permanent magnet machines with multiple rotors or stators relatively rotated for vectorially combining the excitation fields or the armature voltages H02K21/029)} - B64D 27/10: of gas-turbine type (jet aircraft B64D27/16) - B64D 27/33: Hybrid electric aircraft - B64D 27/35: Arrangements for on-board electric energy production, distribution, recovery or storage - F02C 6/20: Adaptations of gas-turbine plants for driving vehicles - H02K 7/1823: {structurally associated with turbines or similar engines} - H02K 21/14: with magnets rotating within the armatures - H02K 21/28: with armatures rotating within the magnets - B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)} - F05D 2220/76: an electrical generator - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - H02K: DYNAMO-ELECTRIC MACHINES (dynamo-electric relays H01H53/00; conversion of DC or AC input power into surge output power {H03K3/53}) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN 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) - 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 An aeronautical turbogenerator for hybrid electric propulsion includes a heat engine and an electrical generator coupled mechanically to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, at least two stationary sectors, one of which covers axially at least two movable annular rings, being arranged angularly so as not to mutually coincide and thus deliver at least two distinct and independent voltage levels. ## Claims ### Claim 1 A turbogenerator for hybrid electric aeronautical propulsion comprising: a heat engine an electrical generator mechanically coupled to the heat engine and including a rotor and a stator, the rotor extending in an axial direction and including a common magnetized rotor yoke comprising a plurality of permanent magnets defining at least three axially distributed movable annular rings, the stator including a magnetic stator yoke comprising a plurality of electrical windings defining axially and/or circumferentially distributed stationary sectors, wherein at least two stationary sectors, including one covering axially at least two movable annular rings, are further arranged angularly so as not to coincide with one another and thus deliver at least two distinct and independent voltage levels. ### Claim 2 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein at least one stationary sector has axially a dimension that is different from another stationary stator sector. ### Claim 3 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein, to a rotor movable annular ring with a determined axial dimension, corresponds a stationary stator sector with a different axial dimension. ### Claim 4 (depends on 2) The aeronautical turbogenerator according to claim 2, wherein a portion of a first stationary stator sector and a portion of a second stationary stator sector are both associated to a rotor movable annular ring. ### Claim 5 (depends on 4) The aeronautical turbogenerator according to claim 4, wherein the stationary stator sectors are spaced by a simple air gap or by obstacles forming walls. ### Claim 6 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein the stationary stator sectors are even in number and arranged symmetrically on either side of a longitudinal axis of the electrical generator. ### Claim 7 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein the stationary stator sectors are arranged asymmetrically relative to a longitudinal axis of the electrical generator. ### Claim 8 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein the heat engine is a gas turbine or an internal-combustion engine. ### Claim 9 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein the rotor has one of the following magnetizations: radial, parallel or Halbach type. ### Claim 10 (depends on 1) The aeronautical turbogenerator according to claim 1, wherein the stator has a diametrical or concentric winding.