Patents by Inventor Dominique Raulin
Dominique Raulin 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).
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Patent number: 11725822Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).Type: GrantFiled: May 28, 2019Date of Patent: August 15, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Nicolas Lunel, Damien Bonnefoi, Christophe Pieussergues, Luc Namer, Dominique Raulin, Dan Ranjiv Joory, Benjamin Frantz Karl Villenave
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Patent number: 10883374Abstract: A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.Type: GrantFiled: September 27, 2016Date of Patent: January 5, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie Notarianni, Jeremy Guivarc'H, Frederic Jean-Bernard Pouzadoux, Dominique Raulin, Thibault Ruf
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Publication number: 20190383489Abstract: The invention concerns a turbo engine comprising a combustion chamber (110) arranged inside the outer housing (112) and comprising an internal revolution wall (118) and an external revolution wall (116). First stop parts (54) and second stop parts (56) fixed respectively to the outer housing and to the combustion chamber are provided, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs (58).Type: ApplicationFiled: May 28, 2019Publication date: December 19, 2019Inventors: Romain Nicolas LUNEL, Damien BONNEFOI, Christophe PIEUSSERGUES, Luc NAMER, Dominique RAULIN, Dan Ranjiv JOORY, Benjamin Frantz Karl VILLENAVE
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Patent number: 10100859Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.Type: GrantFiled: April 8, 2015Date of Patent: October 16, 2018Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pierre Savoyat, Jean-Paul Bourgeois, Bruno Dambrine, François Marlin, Dominique Raulin, Régis Servant
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Publication number: 20180274375Abstract: A blade including a blade body made of organic matrix composite material and a leading edge shield made of a material that withstands point impacts better than the composite material of the blade body. The blade includes a blade tip. The leading edge shield is assembled on the blade body and includes a pressure-side fin and a suction-side fin. The pressure-side fin includes a pressure-side tab and the suction-side fin includes a suction-side tab, the pressure-side tab and the suction-side tab are folded one on the other and being secured to each other so as to form a partial covering of the blade tip. A turbojet includes a fan including such blades, and also a method of fabricating such a blade.Type: ApplicationFiled: September 27, 2016Publication date: September 27, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Gilles Pierre-Marie NOTARIANNI, Jeremy GUIVARC'H, Frederic Jean-Bernard POUZADOUX, Dominique RAULIN, Thibault RUF
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Patent number: 9879552Abstract: A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection.Type: GrantFiled: September 30, 2011Date of Patent: January 30, 2018Assignee: SNECMAInventors: Frédéric Brettes, Alain François Jean Lavie, Dominique Raulin
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Publication number: 20170037887Abstract: An assembly (110) comprising a core (113) and at least a first sheet (111) held on one side of the core by a rivet (120), the rivet having two ends (121, 122). At least a first one of these ends (121, 122) is flared in shape and extends at least through the entire thickness of the first sheet (111, 112). A method of fabricating such an assembly, in which: a core (113) and a first sheet (111) are provided; the first sheet (111) is placed on one side of the core (113); and the core (113) and the first sheet (111) are riveted together.Type: ApplicationFiled: April 8, 2015Publication date: February 9, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Pierre SAVOYAT, Jean-Paul BOURGEOIS, Bruno DAMBRINE, François MARLIN, Dominique RAULIN, Régis SERVANT
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Patent number: 9556745Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.Type: GrantFiled: July 17, 2012Date of Patent: January 31, 2017Assignee: SNECMAInventors: Thierry Georges Paul Papin, Lise Lacroix, Dominique Raulin
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Publication number: 20140193250Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.Type: ApplicationFiled: July 17, 2012Publication date: July 10, 2014Applicant: SNECMAInventors: Thierry Georges Paul Papin, Lise Lacroix, Dominique Raulin
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Patent number: 8740556Abstract: A structural and aerodynamic module including two blades each extending along a longitudinal axis, in which each blade includes a leading edge, a trailing edge, a radially inner edge, and a radially outer edge, is provided. The module also includes a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream. The two blades and the platforms are made from a composite material and the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies.Type: GrantFiled: February 22, 2011Date of Patent: June 3, 2014Assignee: SNECMAInventors: Thierry Georges Paul Papin, Alain Raffy, Dominique Raulin
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Patent number: 8646744Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.Type: GrantFiled: May 14, 2009Date of Patent: February 11, 2014Assignee: SNECMAInventors: Thierry Francois Maurice Duchatelle, Thierry Georges Paul Papin, Dominique Raulin, Arnaud Sanchez
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Publication number: 20130199167Abstract: A hydraulic device for changing the pitch of a propeller including a piston rod actuated by a hydraulic fluid, the piston rod including at its end a clevis mount able to provide a connection for transmitting the movements of the piston rod so as to change the pitch of at least one propeller, a thread nut held in position on the clevis of the piston rod by a fastener, the nut being able to collaborate with a threaded rod in order to provide a connection.Type: ApplicationFiled: September 30, 2011Publication date: August 8, 2013Applicant: SNECMAInventors: Frédéric Brettes, Alain François Jean Lavie, Dominique Raulin
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Patent number: 8052381Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).Type: GrantFiled: December 12, 2008Date of Patent: November 8, 2011Assignee: SNECMAInventors: Antoine Robert Alain Brunet, Claude Chomel, Sebastien Juste, Emmanuel Houradou, Dominique Raulin, Frederic Renault, Julien Sedlak
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Patent number: 8038387Abstract: A bearing for a turbomachine variable pitch stator vane pivot mounted in a bore of the turbomachine casing is disclosed. The bearing includes an inner bushing secured to the pivot and an outer bushing secured to the bore. An elastomeric material is inserted between the inner bushing and the outer bushing to allow the vane to pivot about its axis and absorb at least some of the flexing of the pivot at right angles to the axis. The design makes it possible to reduce bearing bushing wear.Type: GrantFiled: June 20, 2007Date of Patent: October 18, 2011Assignee: SNECMAInventors: Emmanuel Houradou, Herve Hulin, Sebastien Juste, Dominique Raulin
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Publication number: 20110229326Abstract: The invention relates to a structure and aerodynamic module comprising two blades each extending along a longitudinal axis, each blade each comprising a leading edge, a trailing edge, a radially inner edge and a radially outer edge, the module also comprising a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream, the two blades and the platforms being made from a composite material and the two blades being fixed on the radially outer and inner platforms using screw-nut assemblies.Type: ApplicationFiled: February 22, 2011Publication date: September 22, 2011Applicant: SNECMAInventors: Thierry Georges Paul PAPIN, Alain Raffy, Dominique Raulin
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Publication number: 20110073745Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.Type: ApplicationFiled: May 14, 2009Publication date: March 31, 2011Applicant: SNECMAInventors: Thierry François Maurice Duchatelle, Thierry Georges Paul Papin, Dominique Raulin, Arnaud Sanchez
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Publication number: 20090202341Abstract: The invention relates to a turbomachine module comprising a device to improve radial clearances, comprising an outer casing (22), an inner casing (21) and at least one shock absorbing ring (5) connecting the casings, the module also comprising an annular cavity (43) on the downstream side of the ring (5), with a passage (42) formed in it through which an airflow (4) is drawn off from the primary flow (Fp). According to the invention, the device to improve radial clearances comprises a thermal inertia control device for the shock absorbing ring mounted on the shock absorbing ring (5), downstream from it, this device comprising at least one coat of thermal insulation (8), and at least partly delimiting the annular cavity (43) on the downstream side of it (43).Type: ApplicationFiled: December 12, 2008Publication date: August 13, 2009Applicant: SNECMAInventors: Antoine Robert, Alain BRUNET, Claude CHOMEL, Sebastien JUSTE, Emmanuel HOURADOU, Dominique RAULIN, Frederic RENAULT, Julien SEDLAK
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Patent number: 7530784Abstract: A device for controlling variable-pitch vanes in a turbomachine has rods each having at one end a finger for mounting in a control ring and at its other end an assembly orifice for mounting on a drive square of a vane, the axis of the vane being inclined relative to the axis of the finger of the rod, and the assembly orifice in the rod presenting a dimension in the longitudinal direction of the rod that is greater than that of the drive square, and co-operating therewith to define clearance that varies over the height of the drive square and of the orifice.Type: GrantFiled: February 1, 2006Date of Patent: May 12, 2009Assignee: SNECMAInventors: Francois Pierre Georges Maurice Ribassin, Dominique Raulin
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Publication number: 20080031730Abstract: The present invention relates to a bearing (20) for a turbomachine variable pitch stator vane pivot (14) mounted in a bore of the turbomachine casing, and which comprises an inner bushing (22) secured to said pivot and an outer bushing (21) secured to said bore, an elastomeric material (23) being inserted between the inner bushing and the outer bushing to allow the vane to pivot about its axis (XX) and absorb at least some of the flexing of the pivot at right angles to the axis. The design makes it possible to reduce bearing bushing wear.Type: ApplicationFiled: June 20, 2007Publication date: February 7, 2008Applicant: SNECMAInventors: Emmanuel Houradou, Herve Hulin, Sebastien Juste, Dominique Raulin
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Publication number: 20060285969Abstract: A device for controlling variable-pitch vanes in a turbomachine has rods each having at one end a finger for mounting in a control ring and at its other end an assembly orifice for mounting on a drive square of a vane, the axis of the vane being inclined relative to the axis of the finger of the rod, and the assembly orifice in the rod presenting a dimension in the longitudinal direction of the rod that is greater than that of the drive square, and co-operating therewith to define clearance that varies over the height of the drive square and of the orifice.Type: ApplicationFiled: February 1, 2006Publication date: December 21, 2006Applicant: SNECMAInventors: Francois Maurice Ribassin, Dominique Raulin