Patents by Inventor Boris Pierre Marcel MORELLI
Boris Pierre Marcel MORELLI has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Publication number: 20240092479Abstract: A mechanical speed reducer, in particular for a device for driving at least one wheel of an aircraft landing gear, this reducer including a first sun gear including external toothing, first planet gears meshed with the external toothing of the first sun gear, these first planet gears being carried by a first planet carrier, a stationary ring gear meshed with the planet gears, and second planet gears meshed with a ring gear and with an external toothing of said first planet carrier, these second planet gears being carried by a second planet carrier.Type: ApplicationFiled: September 13, 2023Publication date: March 21, 2024Inventors: Maxime FERNANDEZ, Loic FRANCOIS, Boris Pierre Marcel MORELLI, Jordane Emile Andre PELTIER
-
Publication number: 20240092477Abstract: A device for driving at least one wheel of an aircraft landing gear including at least one landing gear wheel, this wheel including a rim, an electric motor including a shaft, a mechanical transmission system between the shaft of the motor and the rim, this mechanical transmission system including a mechanical reducer including a sun gear secured in rotation to the shaft of the motor, a ring gear, and planet gears which are carried by a planet carrier and which each includes three external toothings, including a median external toothing which is meshed with a toothing of the sun gear, and two lateral external toothings which are respectively meshed with toothings of the ring gear.Type: ApplicationFiled: August 29, 2023Publication date: March 21, 2024Inventors: Maxime FERNANDEZ, Loic FRANCOIS, Boris Pierre Marcel MORELLI, Jordane Emile Andre PELTIER
-
Publication number: 20240092480Abstract: A device for driving at least one wheel of an aircraft landing gear is provided. The device includes at least one wheel having a rim, an electric motor having a shaft, and a mechanical transmission system for mechanical transmission between the shaft of the motor and the rim. The mechanical transmission system includes a mechanical reduction gear. The mechanical reduction gear includes a sun gear secured in rotation to the shaft and having an external toothing, a stationary ring gear with internal toothing, a movable ring gear secured in rotation to the rim and having an internal toothing, and planet gears that are meshed with the sun gear and each have two external toothing meshed respectively with the toothing of the stationary and movable ring gears.Type: ApplicationFiled: September 14, 2023Publication date: March 21, 2024Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Maxime Fernandez, Yohan Douy, Loïc Francois, Boris Pierre Marcel Morelli, Jordane Emile André Peltier
-
Patent number: 11933229Abstract: Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.Type: GrantFiled: February 6, 2023Date of Patent: March 19, 2024Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Patrice Julien Ptaszynski, Antoine Jacques Marie Pennacino, Boris Pierre Marcel Morelli
-
Publication number: 20240043134Abstract: A propulsion assembly for an aircraft comprising at least two electric motors configured to be disposed in a wing of the aircraft and each comprising a rotor having a motor shaft movable about a motor axis, at least one propeller borne by a propeller shaft movable about a propeller axis and mechanically coupled to the motor shaft of the at least two electric motors, the propeller axis being perpendicular to the motor axis of the at least two electric motors.Type: ApplicationFiled: February 1, 2022Publication date: February 8, 2024Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Clément RAUCOULES, Boris Pierre Marcel MORELLI, Jordane Emile André PELTIER
-
Patent number: 11802514Abstract: An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.Type: GrantFiled: July 7, 2020Date of Patent: October 31, 2023Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Clément Paul René Niepceron, Boris Pierre Marcel Morelli
-
Publication number: 20230340912Abstract: A mechanical reducer for a turbomachine for an aircraft, this reducer having a sun gear with internal splines and an external toothing, a ring gear which extends around the sun gear and which has an internal toothing, planet gears which are arranged between the sun gear and the ring gear and which each have at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, and a planet carrier which carries first bearings for guiding the planet gears in rotation. The reducer can further include at least one second bearing for guiding the sun gear in rotation. The at least one second bearing can be mounted between the sun gear and the planet carrier.Type: ApplicationFiled: April 21, 2023Publication date: October 26, 2023Inventors: Adrien Louis SIMON, Luc Henri CHATENET, Boris Pierre Marcel MORELLI, Jonathan Jean-Pierre ROUFFET
-
Patent number: 11754002Abstract: The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.Type: GrantFiled: July 7, 2020Date of Patent: September 12, 2023Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Clément Paul René Niepceron, Boris Pierre Marcel Morelli
-
Patent number: 11732608Abstract: Lubricating oil distributor for a mechanical reduction gear of a turbine engine, in particular of an aircraft, wherein it has a general annular shape around an axis X and is formed of a single part, the distributor including first and second independent oil circuits, the first oil circuit including a first oil inlet connected by a first annular chamber to several oil outlets, and the second oil circuit including a second oil inlet connected by a second annular chamber to several oil outlets, the first chamber including a section that is at least partially nested in a section of the second chamber.Type: GrantFiled: December 20, 2019Date of Patent: August 22, 2023Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Mathieu Jean Charrier, Gilles Gaston Jacques Gouin, Boris Pierre Marcel Morelli
-
Publication number: 20230250761Abstract: Speed reduction gear for an aircraft turbomachine. The reduction gear has a main axis and planet carrier having a cage and a cage carrier, a sun gear located in the cage and centred on the main axis, an annular row of planet gears arranged around the main axis and the sun gear and meshed with the sun gear, and a ring gear arranged around the axis and the cage and meshed with the planet gears. The cage and the cage carrier are connected to each other by connections whose bending flexibility is optimised.Type: ApplicationFiled: February 6, 2023Publication date: August 10, 2023Inventors: Patrice Julien PTASZYNSKI, Antoine Jacques Marie PENNACINO, Boris Pierre Marcel MORELLI
-
Publication number: 20230203963Abstract: A turbomachine includes a fan, a first casing with longitudinal axis X in which a motor shaft is rotated around the longitudinal axis X, a second casing surrounding and coaxial with the first casing, and a drive shaft connected to the motor shaft. The driveshaft is also connected to at least two electric machines via a power transmission angle gear device housed in a housing. The electric machines being intended are configured to take or inject power on the motor shaft. The housing has a coupling surface to which the two electric machines are coupled.Type: ApplicationFiled: May 19, 2021Publication date: June 29, 2023Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Jordane Emile André PELTIER, Boris Pierre Marcel MORELLI
-
Patent number: 11686217Abstract: An oil collector for a torque transmission device of an aircraft turbine engine, this oil collector being configured to collect sprayed oil, wherein it includes at least one wall formed at least in part by a mesh structure, and at least one recovery device located at one end of the wall and configured to recover the oil captured by the wall and intended to flow from this wall to the recovery device.Type: GrantFiled: November 10, 2021Date of Patent: June 27, 2023Assignees: SAFRAN, SAFRAN TRANSMISSION SYSTEMSInventors: Boris Pierre Marcel Morelli, Xavier Roger Betbeder-Lauque, Mathieu Jean Charrier
-
Patent number: 11578664Abstract: An oil collector for a mechanical reduction gear of a turbomachine, in particular for an aircraft, the reduction gear including a body having two opposite lateral faces configured to extend in part around planet gears of the reduction gear, the collector further including an internal oil circulation cavity connected firstly to oil inlets located on the faces, and on the other hand to at least one oil outlet, characterised in that at least one of the faces comprises includes columns and rows of several inlets each having a recess with a progressively increasing cross-section, each recess being delimited by walls, at least some of the walls having a hydrodynamic profile.Type: GrantFiled: July 14, 2020Date of Patent: February 14, 2023Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Mathieu Jean Charrier, Boris Pierre Marcel Morelli, Jean-Pierre Serey
-
Patent number: 11448084Abstract: A mechanical reduction gear for a turbomachine, in particular for an aircraft, including a first sun gear having a central axis forming a main axis of the reduction gear, a ring gear, planet gears, a planet carrier, and at least one electric generator, in which the electric generator has a first set of electromagnetic elements and a second set of electromagnetic elements, wherein one among the first and second set of electromagnetic elements is a first set of coils, each coil of this first set of coils being wound around a direction parallel to the main axis, and in which the other among the first and second set of electromagnetic elements is configured to induce a current in the first set of coils when it is driven with a relative movement with respect to the first set of coils.Type: GrantFiled: January 5, 2021Date of Patent: September 20, 2022Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Clément Paul René Niepceron, Boris Pierre Marcel Morelli, Florian Rappaport, Bernard Guy Antoine Charpentier
-
Publication number: 20220268215Abstract: The invention relates to an epicyclic reduction gear for a turbomachine, including a sun wheel that is rotatable about a first axis (A); a ring gear surrounding the sun wheel and being rotatable about the first axis (A); at least one planetary gear that is rotatable about a second axis (B), the planetary gear being meshed with the sun wheel and the ring gear; an immobile planet carrier, the planetary gear being rotatably guided about the second axis (B) with respect to a bearing of the planet carrier; an item of equipment including a rotor. The invention is characterized in that the item of equipment is fastened to the bearing of the planet carrier and the rotor of the item of equipment is rotatably driven by the planetary gear.Type: ApplicationFiled: July 7, 2020Publication date: August 25, 2022Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Clément Paul René Niepceron, Boris Pierre Marcel Morelli
-
Publication number: 20220260021Abstract: An epicyclic reduction gear for a turbomachine includes a sun gear that is rotatable about a first axis and a ring gear surrounding the sun gear and also rotatable about the first axis. The ring gear is secured to a ring gear carrier that rotates a fan shaft. At least one planet gear is rotatable about a second axis and is meshed with the sun gear and the ring gear. The planet gear is guided in rotation about the second axis relative to a bearing of the planet carrier. A piece of equipment comprising a rotor. The piece of equipment is attached to the bearing of the planet carrier and has a rotor rotated by the ring gear carrier.Type: ApplicationFiled: July 7, 2020Publication date: August 18, 2022Applicant: SAFRAN TRANSMISSION SYSTEMSInventors: Clément Paul René NIEPCERON, Boris Pierre Marcel MORELLI
-
Patent number: 11396940Abstract: A lubricant nozzle for a planetary gear set speed reducer of a turbomachine, the nozzle having a generally elongate shape and including a body with a longitudinal axis B, the body having a longitudinal inner cavity in fluid communication with a lubricant inlet located at a longitudinal end of the body and with lubricant outlet apertures that are provided in an annular wall of the body and that extend substantially radially relative to axis B, wherein the apertures are formed in at least one boss of the body, which boss projects radially outwards on the wall and extends, about the axis, at an angular extent that does not exceed 180°.Type: GrantFiled: July 20, 2018Date of Patent: July 26, 2022Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Jean-Charles Michel Pierre Di Giovanni, Alexis Claude Michel Dombek, Boris Pierre Marcel Morelli
-
Patent number: 11370551Abstract: A propulsion unit for an aircraft, including an engine and a propeller shaft and further a propeller with airfoils which is coupled to the propeller shaft and having electrical members consuming electrical power, sealing between a case and the propeller shaft being ensured by a dynamic seal housed between a rotating dynamic seal support secured to the propeller shaft and a dynamic seal support flange secured to an end portion of the case, the rotating dynamic seal support being secured to the propeller shaft and abutted against a bearing for supporting this propeller shaft, it is provided that the propulsion unit, in order to deliver electrical power to the electrical members, having a rotating transformer rotated by the propeller shaft and including a stator, a casing of which is secured to the dynamic seal support flange and a rotor, a casing of which is secured to this propeller shaft.Type: GrantFiled: April 4, 2019Date of Patent: June 28, 2022Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN ELECTRICAL & POWER, SAFRAN TRANSMISSION SYSTEMSInventors: Mathieu Jean Jacques Santin, Guillaume Julien Beck, Aldric Renaud Gabriel Marie Moreau De Lizoreux, Boris Pierre Marcel Morelli, Jean-Michel Bernard Paul Chastagnier, Thomas Turchi
-
Patent number: 11339869Abstract: A lubricating and cooling core for a mechanical reduction gear of a turbine engine, for example of an aircraft, is configured to be mounted in an axis of a planet gear of the reduction gear. The core includes first and second coaxial and substantially frusto-conical shields, each having a first end with a greater diameter and a second opposite end with a smaller diameter, the shields being secured to one another by their second ends and being configured to extend inside the axis and to cover at least a radially internal surface of the axis to define with the latter at least one annular cavity for the circulation of oil for lubricating and cooling the axis, the second ends of the first and second shields having fluid connection means configured to connect the at least one cavity to a source of lubricating and cooling oil.Type: GrantFiled: November 21, 2019Date of Patent: May 24, 2022Assignee: SAFRAN TRANSMISSION SYSTEMSInventors: Adrien Louis Simon, Jean-Charles Michel Pierre Di Giovanni, Boris Pierre Marcel Morelli
-
Publication number: 20220154598Abstract: An oil collector for a torque transmission device of an aircraft turbine engine, this oil collector being configured to collect sprayed oil, wherein it includes at least one wall formed at least in part by a mesh structure, and at least one recovery device located at one end of the wall and configured to recover the oil captured by the wall and intended to flow from this wall to the recovery device.Type: ApplicationFiled: November 10, 2021Publication date: May 19, 2022Inventors: Boris Pierre Marcel MORELLI, Xavier Roger BETBEDER-LAUQUE, Mathieu Jean CHARRIER