Patents by Inventor Frédérick Millon
Frédérick Millon 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: 11384998Abstract: A holding system (101, 102, 103) for holding at least one pipe, comprising a comb including a bar and parallel teeth perpendicular to the bar. A blocking device (30) consisting essentially of a pin, serves to prevent a pipe passing between two of the teeth from moving away from the bar. The holding system further comprises two supports (40A, 40B), positioned at the ends of the comb, and which hold the comb so as to allow rotation thereof around the axis of the bar. A method for mounting a heat exchanger (100) comprising such a holding system.Type: GrantFiled: March 3, 2015Date of Patent: July 12, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Dominique Le Louedec, Arnaud Sternchuss, Nicolas Ravier, Frederick Millon, Bruno Bucher
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Patent number: 10578056Abstract: A nozzle (1) for a space vehicle engine (M), the nozzle comprising a stationary portion (2) and a movable portion (3), the nozzle (1) including a pneumatic deployment system (4) comprising: a deployment actuator (5) for deploying the movable portion (3) of the nozzle (1); a high unlocking actuator (6); a low unlocking actuator (7); and an ejector (41); the deployment system (4) including a feed system (8) configured so as to, sequentially: move the deployment actuator (5) from its support position towards its deployment position; move the high and low unlocking actuators (6, 7) into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system (4) from the nozzle (1).Type: GrantFiled: October 2, 2015Date of Patent: March 3, 2020Assignee: ARIANEGROUP SASInventors: Robert Gazave, Frédérick Millon, Jacques Lelong
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Patent number: 10408366Abstract: A fastening method for fastening a tube (50) to a connector (101, 102), the method comprising the following steps: a) providing a connection kit comprising a sleeve, and a coupling for connecting together at least one pair of tubes, of generally tubular shape; b) placing the coupling in a first position in which the first end of the coupling projects outside the sleeve through a first end (10A) thereof; c) then fastening the first tube in leaktight manner to the first orifice; d) moving the coupling relative to the sleeve into a second position in which the first orifice lies inside the sleeve; and e) with the coupling in the second position, fastening the sleeve (10) at a sufficient distance from the coupling (20). A connection kit for performing the method.Type: GrantFiled: November 17, 2014Date of Patent: September 10, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Dominique Le Louëdec, Carine Dorion, Bruno Bucher, Frederick Millon
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Patent number: 10371309Abstract: An assembly comprising a duct (1) for passing a flow of cryogenic fluid, and a valve (2); the assembly being characterized in that the duct (1) includes an interface for inserting the valve, the interface forming an internal abutment (51) and an external abutment (52); the valve (2) being configured in such a manner as to be inserted into said insertion interface by sliding, the valve (2) comprising a valve body (3) presenting a first end (31) and a second end (32), the valve body (3) being adapted to be bolted in said insertion interface in such a manner that the first end (31) and the second end (32) come into abutment respectively against the internal abutment (51) and against the external abutment (52), the assembly including an internal sealing element (61) arranged between the internal abutment (51) and the first end (31), and an external sealing element (62) arranged between the external abutment (52) and the second end (32).Type: GrantFiled: March 18, 2015Date of Patent: August 6, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Robert Gazave, Frédérick Millon
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Patent number: 10190592Abstract: A turbopump includes a turbine fed with hot gas, a pump driven by the turbine and fed with liquid fluid, and a hot gas exhaust pipe situated downstream from the turbine. The turbopump includes a bleed-and-injection circuit including a bleeder for bleeding the liquid fluid at the outlet from the pump, a heater for heating the liquid fluid as bled off in this way so as to transform it into gaseous fluid, and an injector for injecting the gaseous fluid into an interface region of the turbopump situated between the pump and the turbine, so as to optimize the flow and temperature conditions of the fluid entering into the turbine cavity in order to eliminate the vibratory phenomena that result from interaction between the fluid and the turbine disk.Type: GrantFiled: May 14, 2014Date of Patent: January 29, 2019Assignee: ARIANEGROUP SASInventors: Dominique Le Louedec, Guillaume Chemla, Philippe Even, Frederick Millon, Laurent Collongeat
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Publication number: 20170306889Abstract: A nozzle (1) for a space vehicle engine (M), the nozzle comprising a stationary portion (2) and a movable portion (3), the nozzle (1) including a pneumatic deployment system (4) comprising: a deployment actuator (5) for deploying the movable portion (3) of the nozzle (1); a high unlocking actuator (6); a low unlocking actuator (7); and an ejector (41); the deployment system (4) including a feed system (8) configured so as to, sequentially: move the deployment actuator (5) from its support position towards its deployment position; move the high and low unlocking actuators (6, 7) into their high and low unlocking positions; and actuate the ejector so as to eject the deployment system (4) from the nozzle (1).Type: ApplicationFiled: October 2, 2015Publication date: October 26, 2017Applicant: AIRBUS SAFRAN LAUNCHERS SASInventors: Robert GAZAVE, Frédérick MILLON, Jacques LELONG
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Publication number: 20170184247Abstract: An assembly comprising a duct (1) for passing a flow of cryogenic fluid, and a valve (2); the assembly being characterized in that the duct (1) includes an interface for inserting the valve, the interface forming an internal abutment (51) and an external abutment (52); the valve (2) being configured in such a manner as to be inserted into said insertion interface by sliding, the valve (2) comprising a valve body (3) presenting a first end (31) and a second end (32), the valve body (3) being adapted to be bolted in said insertion interface in such a manner that the first end (31) and the second end (32) come into abutment respectively against the internal abutment (51) and against the external abutment (52), the assembly including an internal sealing element (61) arranged between the internal abutment (51) and the first end (31), and an external sealing element (62) arranged between the external abutment (52) and the second end (32).Type: ApplicationFiled: March 18, 2015Publication date: June 29, 2017Inventors: Robert Gazave, Frederick Millon
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Publication number: 20170059258Abstract: A holding system (101, 102, 103) for holding at least one pipe, comprising a comb including a bar and parallel teeth perpendicular to the bar. A blocking device (30) consisting essentially of a pin, serves to prevent a pipe passing between two of the teeth from moving away from the bar. The holding system further comprises two supports (40A, 40B), positioned at the ends of the comb, and which hold the comb so as to allow rotation thereof around the axis of the bar. A method for mounting a heat exchanger (100) comprising such a holding system.Type: ApplicationFiled: March 3, 2015Publication date: March 2, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Dominique LE LOUEDEC, Amaud STERNCHUSS, Nicolas RAVIER, Frederick MILLON, Bruno BUCHER
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Publication number: 20160377201Abstract: A fastening method for fastening a tube (50) to a connector (101, 102), the method comprising the following steps: a) providing a connection kit comprising a sleeve, and a coupling for connecting together at least one pair of tubes, of generally tubular shape; b) placing the coupling in a first position in which the first end of the coupling projects outside the sleeve through a first end (10A) thereof; c) then fastening the first tube in leaktight manner to the first orifice; d) moving the coupling relative to the sleeve into a second position in which the first orifice lies inside the sleeve; and e) with the coupling in the second position, fastening the sleeve (10) at a sufficient distance from the coupling (20). A connection kit for performing the method.Type: ApplicationFiled: November 17, 2014Publication date: December 29, 2016Applicant: SNECMAInventors: Dominique LE LOUËDEC, Carine DORION, Bruno BUCHER, Frederick MILLON
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Publication number: 20160169240Abstract: A turbopump includes a turbine fed with hot gas, a pump driven by the turbine and fed with liquid fluid, and a hot gas exhaust pipe situated downstream from the turbine. The turbopump includes a bleed-and-injection circuit including a bleeder for bleeding the liquid fluid at the outlet from the pump, a heater for heating the liquid fluid as bled off in this way so as to transform it into gaseous fluid, and an injector for injecting the gaseous fluid into an interface region of the turbopump situated between the pump and the turbine, so as to optimize the flow and temperature conditions of the fluid entering into the turbine cavity in order to eliminate the vibratory phenomena that result from interaction between the fluid and the turbine disk.Type: ApplicationFiled: May 14, 2014Publication date: June 16, 2016Applicant: SNECMAInventors: Dominique LE LOUEDEC, Guillaume CHEMLA, Philippe EVEN, Frederick MILLON, Laurent COLLONGEAT
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Patent number: 8281599Abstract: The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold.Type: GrantFiled: June 22, 2009Date of Patent: October 9, 2012Assignee: SNECMAInventors: Philippe Even, Philippe Beauverger, Christelle Branchet, Frédérick Millon
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Publication number: 20090314895Abstract: The invention relates to a device for damping the lateral forces due to jet separation that act on a rocket engine nozzle during a stage of starting or stopping the engine, the engine including at least two identical drive assemblies mounted on the nozzle to take up the lateral forces acting thereon, each drive assembly comprising a first member forming a strut, a second member forming an anchor structure, and an actuator. Each strut comprises means enabling it to act as a rigid strut so long as the lateral forces acting on the corresponding actuator remain below a determined force threshold, and as an element for peak limiting force and for dissipating residual kinetic energy once the forces acting on the actuator exceed the determined force threshold.Type: ApplicationFiled: June 22, 2009Publication date: December 24, 2009Applicant: SNECMAInventors: Philippe Even, Philippe Beauverger, Christelle Branchet, Frederick Millon