Patents by Inventor Thierry Georges Paul Papin

Thierry Georges Paul Papin 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: 20240102422
    Abstract: Discharge valve of an aircraft turbomachine, including a discharge gate intended to be mounted pivotably about an axis between a position for closing an air passage orifice and an open position of said orifice, the orifice being formed in an intermediate casing of the turbomachine, the discharge valve including a sealing device having a seal configured to be movably mounted on the intermediate casing and a movement system configured to move the seal between a first position in which the seal is intended to bear against the discharge gate when the gate is in a closure position, and a second position in which the seal is retracted with respect to the air passage orifice when the discharge gate is in an open position.
    Type: Application
    Filed: January 21, 2022
    Publication date: March 28, 2024
    Inventors: Azath MOHAMED, Alexandre BRANCO, Thierry Georges Paul PAPIN, Virginie Martine COLLIN
  • Publication number: 20230349343
    Abstract: An assembly for an aircraft turbine engine, includes a fan, a speed reduction gear and an intermediate casing including an internal annular structure that houses an epicyclic gear train equipped with a planet carrier. The assembly includes a secondary retention device for the ring gear of the planet carrier, the device including: first projections that project radially inwards from the internal annular structure, each first projection having a recess that is open radially inwards, axially downwards and circumferentially in a first direction; and second projections that project radially outwards from the ring gear of the planet carrier and cooperate with the first projections in such a way that each second projection is partially accommodated in the recess of the first projection with which it is associated and downstream therefrom.
    Type: Application
    Filed: September 1, 2021
    Publication date: November 2, 2023
    Inventors: Thierry Georges Paul PAPIN, Didier Gabriel Bertrand DESOMBRE
  • Patent number: 11780562
    Abstract: The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).
    Type: Grant
    Filed: July 13, 2020
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Cottet, Thierry Georges Paul Papin, Regis Eugene Henri Servant
  • Publication number: 20230294816
    Abstract: An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup, configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.
    Type: Application
    Filed: July 15, 2021
    Publication date: September 21, 2023
    Inventors: Clément COTTET, Vivien Mickaël COURTIER, Vincent JOUDON, Thierry Georges Paul PAPIN
  • Patent number: 11753143
    Abstract: The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ?—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ?—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ?—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller.
    Type: Grant
    Filed: July 16, 2020
    Date of Patent: September 12, 2023
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Clement Cottet, Thierry Georges Paul Papin, Regis Eugene Henri Servant
  • Publication number: 20220289362
    Abstract: The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ?—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ?—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ?—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller.
    Type: Application
    Filed: July 16, 2020
    Publication date: September 15, 2022
    Inventors: Clement COTTET, Thierry Georges Paul PAPIN, Regis Eugene Henri SERVANT
  • Patent number: 11428199
    Abstract: A turbomachine module with a longitudinal axis, the module comprising: a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; a system for changing the pitch of the blades of the propeller comprising: a control, and a mechanism for varying the pitch of the blades of the propeller connecting these blades to the control, wherein the control comprises a rotary actuator comprising a control body and a reference body which is integral with the rotary casing, and wherein the mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by the control body and which is guided in rotation on the rotary casing, the synchronization ring being connected to the blades.
    Type: Grant
    Filed: July 15, 2020
    Date of Patent: August 30, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Régis Eugène Henri Servant, Clément Cottet, Thierry Georges Paul Papin
  • Publication number: 20220135207
    Abstract: The invention relates to a turbomachine module (1), comprising: —a rotating housing (7-8) supporting a propeller provided with a plurality of blades (5), —a system for varying the pitch of the propeller blades (5), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (7-8), in that the control means comprise an annular row of rotary actuators (16), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring (11) that is driven to rotate by rotary output shafts (17) of the actuators (16), the synchronisation ring (11) being guided in rotation relative to the rotary housing (7-8) by guide means and meshed by a first toothing (13) with pinions (14) of the blades (5).
    Type: Application
    Filed: July 13, 2020
    Publication date: May 5, 2022
    Inventors: Clement COTTET, Thierry Georges Paul PAPIN, Regis Eugene Henri SERVANT
  • Publication number: 20220099022
    Abstract: A noise reducing device for an aircraft turbine engine, the device having a structure in the form of a stack of layers, such that a first and a second skin made of composite material form a first and a second outer layer, these outer layers being substantially parallel to one another and enclosing a central layer. The central layer has a honeycomb structure having partitions extending transversely from the first outer layer to the second outer layer so as to form cavities. The partitions are made of viscoelastic material and form an acute angle of inclination (?) with the first and second outer layers.
    Type: Application
    Filed: January 22, 2020
    Publication date: March 31, 2022
    Inventor: Thierry Georges Paul PAPIN
  • Patent number: 11143045
    Abstract: The invention relates to an intermediate case (25) for a twin spool turbomachine for an aircraft, comprising a hub (26), an outer shell (23) and outlet guide vanes (24) installed at their ends on the hub and on the outer shell, and each of at least some of the outlet guide vanes (24) performing a heat exchanger function and comprising a lubricant passage (50a, 50b) designed to be cooled by the fan flow (58) following an outer surface of the outlet guide vane. According to the invention, the case also comprises at least one lubricant duct (55) passing along a circumferential direction of the hub (26) and at least part of which is made from a single casting with the hub, the lubricant duct (55) having at least one lateral opening communicating with the lubricant passage (50a, 50b) of at least one of the vanes (24).
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: October 12, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cédric Zaccardi, Christophe Paul Jacquemard, Thierry Georges Paul Papin, Christophe Marcel Lucien Perdrigeon
  • Patent number: 10907489
    Abstract: A vaned ring for a turbomachine stator includes an outer shell, a vane having a vane head, and two platforms arranged circumferentially on either side of the vane head, and fixed on a radially inner face of the outer shell by detachable fasteners. The vane head has first conical seatings bearing on respective second conical seatings of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring includes a frangible pin including a base mounted on the outer shell and a head projecting radially inwards with respect to the outer shell and having a head surface forming, vis-à-vis a top surface of the vane head, a stop opposing a displacement of the vane radially outwards.
    Type: Grant
    Filed: February 11, 2019
    Date of Patent: February 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Jean-Marc Claude Perrollaz
  • Publication number: 20210017949
    Abstract: A turbomachine module with a longitudinal axis, the module comprising: a rotary casing rotatable around the longitudinal axis and arranged to carry a propeller provided with a plurality of blades; a system for changing the pitch of the blades of the propeller comprising: a control, and a mechanism for varying the pitch of the blades of the propeller connecting these blades to the control, wherein the control comprises a rotary actuator comprising a control body and a reference body which is integral with the rotary casing, and wherein the mechanism for varying the pitch comprises a synchronization ring which is driven in rotation around the longitudinal axis by the control body and which is guided in rotation on the rotary casing, the synchronization ring being connected to the blades.
    Type: Application
    Filed: July 15, 2020
    Publication date: January 21, 2021
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Régis Eugène Henri Servant, Clément Cottet, Thierry Georges Paul Papin
  • Patent number: 10723476
    Abstract: A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.
    Type: Grant
    Filed: November 9, 2018
    Date of Patent: July 28, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cedric Zaccardi, Christophe Marcel Lucien Perdrigeon, Francois Marie Paul Marlin, Thierry Georges Paul Papin, Jacky Novi Mardjono
  • Patent number: 10697312
    Abstract: A guide vane for a twin-spool aircraft turbomachine has an aerodynamic part that includes an internal lubricant cooling passage extending along a principal lubricant flow direction. The aerodynamic part is made in a single piece and also includes heat transfer fins arranged in the passage connecting the intrados and extrados walls and extending approximately parallel to the direction, these fins being distributed in successive rows along the principal direction and made such that for two rows of staggered directly consecutive fins, a first row includes fins forming a positive acute angle A1 with a dummy reference plane, while a second row includes fins forming a negative acute angle A2 with this plane.
    Type: Grant
    Filed: March 7, 2018
    Date of Patent: June 30, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Mohamed-Lamine Boutaleb, Fabien Roger Gaston Caty, Sebastien Vincent Francois Dreano, Thierry Georges Paul Papin, Christophe Marcel Lucien Perdrigeon, Cedric Zaccardi
  • Patent number: 10662974
    Abstract: The invention relates to a guide vane intended to be mounted in a turbine engine between an inner shroud (17) and an outer shroud (16), comprising a longitudinal straightening body (41) for an air flow extending between a first end (42) intended to be positioned at the inner shroud (17) and a second end (44) intended to be positioned at the outer shroud (16), the longitudinal straightening body having an aerodynamic profile defined by a leading edge (41a) and a trailing edge (41b) in the flow direction of the air flow, and by a camber line (41c) extending from the leading edge (41a) to the trailing edge (41b).
    Type: Grant
    Filed: December 1, 2017
    Date of Patent: May 26, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry Georges Paul Papin, Marc-Antoine Anatole Got, Kaelig Merwen Orieux, Cedric Zaccardi
  • Patent number: 10648356
    Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: May 12, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Eric Pierre Georges Le Marechal, Xavier Jean Yves Alain Agneray, Thierry Georges Paul Papin, Mathieu Daniel Marie Van Gansen, Cédric Zaccardi
  • Publication number: 20200024997
    Abstract: A vaned ring for a turbomachine stator includes an outer shell (42), a vane (46) having a vane head (52), and two platforms (60) arranged circumferentially on either side of the vane head, and fixed on a radially inner face (61) of the outer shell by means of detachable fasteners. The vane head has first conical seatings (70) bearing on respective second conical seatings (72) of the two platforms so as to prevent a displacement of the vane radially inwards and along the circumferential direction. The vaned ring comprises a frangible pin (73) including a base (73A) mounted on the outer shell and a head (73B) projecting radially inwards with respect to the outer shell and having a head surface (73C) forming, vis-a-vis a top surface (74) of the vane head, a stop opposing a displacement of the vane radially outwards.
    Type: Application
    Filed: February 11, 2019
    Publication date: January 23, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Jean-Marc Claude Perrollaz
  • Publication number: 20190368372
    Abstract: A bypass turbine engine is described. The engine includes a system for bleeding gas from a primary stream to a secondary stream. The system may include two coaxial rings extending one around the other. A perforated internal first ring may be situated at the level of an outer casing and may extend substantially in a continuation of the outer casing. A perforated external second ring may be mounted such that it slides circumferentially on the first ring between a first position in which the perforations of the rings do not communicate with one another and a second bleed position in which the perforations of the rings communicate with one another.
    Type: Application
    Filed: November 16, 2017
    Publication date: December 5, 2019
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Eric Pierre Georges Le Marechal, Xavier Jean Yves Alain Agneray, Thierry Georges Paul Papin, Mathieu Daniel Marie Van Gansen, Cédric Zaccardi
  • Patent number: 10392955
    Abstract: A turbomachine fan frame including a central hub, a plurality of radial vanes installed on the hub and distributed around the hub, each vane including an inner radial end root at which the vane is fixed to the hub, a plurality of flow stream reconstitution platforms, each platform being installed between the roots of two adjacent vanes and radially at a distance from the hub, wherein each platform is fixed to the hub by at least one support element associated with the platform, the support element located between the associated platform and the hub and located between the roots of two adjacent vanes.
    Type: Grant
    Filed: August 2, 2016
    Date of Patent: August 27, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thierry Georges Paul Papin, Kaelig Merwen Orieux, Virginie Guilbert, Lise Lacroix
  • Patent number: 10392952
    Abstract: A guide vane for a dual flow aircraft turbine engine, the aerodynamic part of the vane including an inner duct for lubricant cooling extending in a main direction and being partly bounded by a pressure side wall and a suction side wall of the vane. A heat conduction matrix is lodged in the duct, and presents main heat transfer wings extending parallel to the direction, and laid out in staggered rows.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: August 27, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Cedric Zaccardi, Mohamed-Lamine Boutaleb, Sebastien Christophe Chalaud, Eric Pierre Georges Lemarechal, Thierry Georges Paul Papin