Patents by Inventor Nicolas Xavier TRAPPIER

Nicolas Xavier TRAPPIER 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: 20210054743
    Abstract: The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).
    Type: Application
    Filed: January 29, 2019
    Publication date: February 25, 2021
    Applicant: Safran Aircraft Engines
    Inventors: Stéphane Pierre Guillaume BLANCHARD, Nicolas Xavier TRAPPIER, Quentin DE RICHAUD
  • Publication number: 20210017880
    Abstract: A turbine shaft of a turbomachine extending along a longitudinal axis (A) includes a main tubular portion with a length L1 and a maximum outer main diameter. The shaft further includes a secondary tubular segment with a length L2 and a maximum outer secondary diameter greater than the maximum outer main diameter. The secondary tubular segment extends radially from the shaft such that the main tubular portion extends on either side of the secondary tubular segment along the longitudinal axis (A). The secondary tubular segment includes a weak point that is configured to break the shaft into two distinct parts when the value of a tangential stress applied to the shaft exceeds a predetermined threshold value, and thus cause retraction of the turbine.
    Type: Application
    Filed: March 20, 2019
    Publication date: January 21, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Nicolas Xavier Trappier, Pierrot Guillou, Caroline Marie Frantz
  • Patent number: 10859000
    Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.
    Type: Grant
    Filed: February 8, 2017
    Date of Patent: December 8, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Patrice Kubiak, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Benoit Jean Henri Gomanne, Arnaud Nicolas Negri, Nicolas Xavier Trappier
  • Publication number: 20200277866
    Abstract: The present invention relates to a rotor (1) of a turbomachine turbine, comprising a rotor disc (2) and a plurality of blades (3) distributed at its periphery, said rotor disc (2) comprising a plurality of mainly axial cells (23), each blade (3) comprising a root (32), retained in one of the cells (23) of said rotor disc, each root being dimensioned so as to form a space (4) between the bottom of the cell (23) and the radially inner face (324) of the root. This rotor is remarkable in that said root comprises a mainly axial blind hole (5) opening onto the upstream face of the root and a plurality of mainly radial air ejection orifices (6), each air ejection orifice (6) opening into said blind hole (5) and onto the radially inner face (324) of the root located facing the bottom of the cell (23).
    Type: Application
    Filed: January 9, 2020
    Publication date: September 3, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Antoine Hervé DOS SANTOS, Quentin DE RICHAUD, Nicolas Xavier TRAPPIER
  • Patent number: 10640222
    Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
    Type: Grant
    Filed: October 10, 2017
    Date of Patent: May 5, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Nora El Ghannam, Matthieu Etienne Attali, Romain Jean-Claude Ferrier, Caroline Marie Frantz, Thomas Gerard Daniel Riviere, Nicolas Xavier Trappier
  • Patent number: 10598031
    Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: March 24, 2020
    Assignee: SAFRAN AIRCTAFT ENGINES
    Inventors: Stéphane Pierre Guillaume Blanchard, Joao Antonio Amorim, Maxime Aurélien Rotenberg, Nicolas Xavier Trappier
  • Publication number: 20190153958
    Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.
    Type: Application
    Filed: February 8, 2017
    Publication date: May 23, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Patrice KUBIAK, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Romain Guillaume CUVILLIER, Benoit Jean Henri GOMANNE, Arnaud Nicolas NEGRI, Nicolas Xavier TRAPPIER
  • Publication number: 20180105278
    Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
    Type: Application
    Filed: October 10, 2017
    Publication date: April 19, 2018
    Inventors: Nora EL GHANNAM, Matthieu Etienne ATTALI, Romain Jean-Claude FERRIER, Caroline Marie FRANTZ, Thomas Gerard Daniel RIVIERE, Nicolas Xavier TRAPPIER
  • Publication number: 20180066528
    Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
    Type: Application
    Filed: September 8, 2017
    Publication date: March 8, 2018
    Inventors: Stéphane Pierre Guillaume BLANCHARD, Joao Antonio AMORIM, Maxime Aurélien ROTENBERG, Nicolas Xavier TRAPPIER