Patents by Inventor Francois Gallet

Francois Gallet 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).

  • Patent number: 11821360
    Abstract: The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.
    Type: Grant
    Filed: July 3, 2019
    Date of Patent: November 21, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Jerome Jean Tantot, Francois Gallet
  • Publication number: 20230356853
    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.
    Type: Application
    Filed: May 20, 2021
    Publication date: November 9, 2023
    Inventors: Michael Cline, Jonathan E. Coleman, Craig W. Higgins, Daniel E. Mollman, Mark E. Linz, Guillaume Glemarec, Valerio Capasso, Jean-Baptiste Manuel Nicolas Vignes, Nicolas Maurice Hervé Aussedat, Francois Gallet
  • Publication number: 20230212251
    Abstract: An isolated polypeptide derived from human sortilin, including an amino acid sequence which has at least 80% identity with the sequence SEQ ID NO 2 Val Leu Ile Val Lys Lys Tyr Val Cys Gly Gly Arg Phe Leu Val Mis Arg Tyr Ser Val Leu Gin Gin Mis Ala Glu Ala Asn Gly Val Asp Gly Val Asp Ala Leu Asp Thr Ala Ser Mis Thr Asn Lys Ser Gly Tyr Mis Asp Asp Ser Asp Glu Asp Leu Leu Glu on condition that the polypeptide does not contain the sequence SEQ ID NO 3 or a sequence having at least 80% identity with the aforementioned sequence SEQ ID NO 3, for use as a drug.
    Type: Application
    Filed: August 10, 2020
    Publication date: July 6, 2023
    Inventors: Camille GRANET, Eric LAPEYRONNIE, Thomas NAVES, Paul-François GALLET, Marie-Odile JAUBERTEAU
  • Publication number: 20220195917
    Abstract: Counter-rotating turbine of a turbomachine extending about an axis of rotation and comprising an inner rotor rotating about the axis of rotation, and comprising at least one inner movable blade rotatably supported by a first shaft, an outer rotor rotating about the axis of rotation in a direction opposite to the inner rotor, and comprising at least one outer movable blade rotatably supported by a second shaft coaxial with the first shaft, the first and second shafts extending axially from upstream to downstream of the turbine, wherein the first shaft is guided in rotation by a first bearing disposed between the first shaft and an upstream casing of the turbine, and the second shaft is guided in rotation by a second bearing disposed between the second shaft and said upstream casing of the turbine.
    Type: Application
    Filed: April 2, 2020
    Publication date: June 23, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: Francois GALLET
  • Patent number: 11280220
    Abstract: A turbomachine including a stator, a rotor mounted on a shaft, a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at the inlet of the turbomachine, the first bearing forming an axial abutment linked to the stator, the second bearing including an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, the second bearing including rolling elements in axial support on the inner ring and on the outer ring. The outer ring includes a radially extending ring portion. The turbomachine also includes an axial force application device mounted between the arm and the ring portion.
    Type: Grant
    Filed: August 27, 2019
    Date of Patent: March 22, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Francois Gallet
  • Patent number: 11125186
    Abstract: The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power turbine (3). The two fans (7, 8) and the turbine (3) are integrated into a nacelle (14) which projects downstream from the fuselage (1) and through which air flows. According to the invention, at least one of the fans (7, 8) of the aircraft and, in particular, the downstream fan (8) comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring (25) in the aircraft is placed upstream of the upstream fan (7). The variable-spacing stator blades (25) and the variable-spacing blades of the downstream fan (8) are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle (14) from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (14).
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: September 21, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Francois Gallet
  • Publication number: 20210140367
    Abstract: The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.
    Type: Application
    Filed: July 3, 2019
    Publication date: May 13, 2021
    Inventors: Nicolas Jerome Jean TANTOT, Francois GALLET
  • Patent number: 10661910
    Abstract: An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: May 26, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: François Gallet
  • Publication number: 20200072081
    Abstract: A turbomachine including a stator, a rotor mounted on a shaft, a first bearing and a second bearing downstream of the first bearing in a direction of air circulation at the inlet of the turbomachine, the first bearing forming an axial abutment linked to the stator, the second bearing including an inner ring secured to the shaft and an outer ring mounted on an arm secured to the stator, the second bearing including rolling elements in axial support on the inner ring and on the outer ring. The outer ring includes a radially extending ring portion. The turbomachine also includes an axial force application device mounted between the arm and the ring portion.
    Type: Application
    Filed: August 27, 2019
    Publication date: March 5, 2020
    Inventor: Francois GALLET
  • Patent number: 10435163
    Abstract: An aircraft propelled by a turbojet having contrarotating fans, the turbojet being incorporated at the rear of a fuselage of the aircraft and in line therewith and including two gas generators that feed a working turbine having two contrarotating turbine rotors for driving two fans arranged downstream from the gas generators, and distinct air intakes for feeding each gas generator, the air intakes being connected to the fuselage of the aircraft so as to take in at least a portion of the boundary layer formed around the fuselage of the aircraft.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: October 8, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: François Gallet
  • Patent number: 10227881
    Abstract: A turbine blade including an airfoil (31) extending above a platform (32) and a root (33) extending below the platform, the root of the blade having the form of a radially extending arm (34), being produced from composite material and including at least one cylindrical face (34). The direction of the generatrices which are oriented in the direction of the platform to allow a clamping piece (5) to slide towards the latter on the cylindrical face under the action of centrifugal force. The arm includes, at its lower end, a protuberance (35) forming a radial bearing point for engagement with an element for retaining the blade on a turbine disc (1). The root (33) is located entirely on the side of the protuberance with respect to the face.
    Type: Grant
    Filed: September 26, 2013
    Date of Patent: March 12, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Francois Gallet
  • Patent number: 10082040
    Abstract: The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: September 25, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Francois Gallet, Nicolas Jerome Jean Tantot
  • Publication number: 20180209443
    Abstract: An aircraft comprising a fuselage and propelled by a turbine engine having two coaxial and contrarotating fans, the turbine engine comprising a power turbine having two contrarotating rotors, one of which drives a fan upstream from the turbine, the other a fan downstream from the turbine, each fan comprising a ring of blades, and the assembly of the fans and the power turbine being incorporated at the rear of the fuselage, in the extension of same. The aircraft comprises, for at least one of the fans, a device for blocking the rotation of the fan and a device configured to modify the pitch of the blades of the fan in such a way as to make it operate as a flow straightener with respect to the other fan.
    Type: Application
    Filed: July 21, 2016
    Publication date: July 26, 2018
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventor: François Gallet
  • Publication number: 20180209380
    Abstract: The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power turbine (3). The two fans (7, 8) and the turbine (3) are integrated into a nacelle (14) which projects downstream from the fuselage (1) and through which air flows. According to the invention, at least one of the fans (7, 8) of the aircraft and, in particular, the downstream fan (8) comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring (25) in the aircraft is placed upstream of the upstream fan (7). The variable-spacing stator blades (25) and the variable-spacing blades of the downstream fan (8) are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle (14) from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (14).
    Type: Application
    Filed: July 21, 2016
    Publication date: July 26, 2018
    Inventor: Francois GALLET
  • Publication number: 20180209294
    Abstract: The invention concerns an aircraft propelled by a turbine engine having contrarotating fans (7, 8), the turbine engine being incorporated at the rear of a fuselage (1) of the aircraft, in the extension of same and comprising at least two gas generators (2a, 2b) that supply, via a shared central stream (4), a power turbine (3), the turbine (3) comprising two contrarotating rotors (5, 6) for driving two fans (7,8) disposed downstream from the gas generators (2a, 2b), said aircraft comprising means (15) arranged for separating the gas flow in the power turbine (3) into at least two concentric streams (16, 17) and a device comprising first means for distributing the gas flow (21-24) between said streams (16, 17) from the central stream (4), the first distribution means being configured to be able to open or close the supply of at least one so-called sealable stream (16) of the streams (16, 17) of the power turbine (3).
    Type: Application
    Filed: July 21, 2016
    Publication date: July 26, 2018
    Inventors: Francois GALLET, Nicolas Jerome Jean TANTOT
  • Patent number: 9995224
    Abstract: A system for supplying pressurized air installed in an aircraft turbine engine, configured to supply pressurization air to a portion of the aircraft for using compressed air from pressurization air collected from a portion for collecting compressed air, characterized in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment.
    Type: Grant
    Filed: July 22, 2015
    Date of Patent: June 12, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: François Gallet
  • Patent number: 9863273
    Abstract: The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterized in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
    Type: Grant
    Filed: August 21, 2014
    Date of Patent: January 9, 2018
    Assignee: SNECMA
    Inventors: Francois Robert Bellabal, Francois Gallet, Mathieu Ange Poisson
  • Patent number: 9856825
    Abstract: A bypass turbojet engine nacelle that forms a fan casing includes a first, upstream, streamlining element and a second streamlining element that forms a jet pipe. The second element can move translationally between a position ensuring aerodynamic continuity of the nacelle and a downstream position uncovering flow reversal openings. A thrust reverser device is housed in the nacelle and includes flow reverser flaps and cascades of vanes providing radial guidance for the flow. The cascades of vanes providing radial guidance for the flow can move in translation along the axis of the nacelle between a retracted position into the first steamlining element and an active flow-guidance position, the second streamlining element being secured to the cascades of vanes, the reverser flaps being mounted to rotate about axes that are transverse with respect to the axis of the nacelle and secured to the cascades of vanes.
    Type: Grant
    Filed: August 8, 2012
    Date of Patent: January 2, 2018
    Assignee: SNECMA
    Inventor: Francois Gallet
  • Patent number: 9738392
    Abstract: A variable geometry suspension structure for suspending a turboprop from a structural element of an aircraft, the structure including a rear cradle for fastening to a structural element of an aircraft and a front cradle for supporting a front portion of the turboprop, the front cradle being connected to the rear cradle, firstly via a pivot connection configured to enable the front cradle to tilt vertically relative to the rear cradle, and secondly by a return spring configured to prevent the front cradle from tilting while thrust from the turboprop is below a predetermined threshold.
    Type: Grant
    Filed: January 15, 2014
    Date of Patent: August 22, 2017
    Assignee: SNECMA
    Inventors: Antoine Hellegouarch, Mathieu Ange Poisson, Francois Gallet
  • Publication number: 20170204789
    Abstract: A system for supplying pressurised air installed in an aircraft turbine engine, configured to supply pressurisation air to a portion of the aircraft for using compressed air from pressurisation air collected from a portion for collecting compressed air, characterised in that it comprises a collection port formed on a casing of the compressed air collection portion, a collection member coupled to the collection port, a through port of the collection member formed on a casing of a compartment of the turbine engine, said casing being subjected to small movements relative to the casing of the compressed air portion, the collection member crossing the through port with a freedom of movement relative to the latter during said small movements, a high-pressure space crossed by the collection member, located between the casing of the compressed air collection portion and the casing of the compartment.
    Type: Application
    Filed: July 22, 2015
    Publication date: July 20, 2017
    Inventor: François Gallet