Patents by Inventor Sylvain Duval
Sylvain Duval 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: 8756935Abstract: A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.Type: GrantFiled: June 10, 2009Date of Patent: June 24, 2014Assignee: SNECMAInventors: Sylvain Duval, Didier Hippolyte Hernandez, Romain Nicolas Lunel
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Patent number: 8516830Abstract: A turbomachine combustion chamber including a substantially L-shaped fuel injector and a device for mounting and fastening the injector in an orifice of the casing of the chamber, is disclosed. The device includes an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing.Type: GrantFiled: August 20, 2009Date of Patent: August 27, 2013Assignee: SNECMAInventors: Sylvain Duval, Didier Hippolyte Hernandez, Romain Nicolas Lunel
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Patent number: 8028530Abstract: A turbomachine including an annular combustion chamber is disclosed. The combustion chamber includes a radially inner wall and a radially outer wall exhibiting symmetry of revolution. An annular chamber end wall equipped with a fuel injection device connects upstream ends of the inner and outer walls. A suspension device suspends the upstream end of the combustion chamber from an outer casing.Type: GrantFiled: July 22, 2008Date of Patent: October 4, 2011Assignee: SNECMAInventors: Patrice Andre Commaret, Sylvain Duval, Didier Hippolyte Hernandez, Yann Francois Jean-Claude Vuillemenot
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Publication number: 20110120144Abstract: An annular combustion chamber for a turbomachine, such as a jet engine or a turboprop engine for an aircraft, including at the downstream end of one of its external or internal walls of revolution an annular flange for fastening to a casing of the turbomachine, the downstream end of the other wall of revolution of the chamber including a bearing mechanism which are spaced apart from another casing of the turbomachine when cold and bear radially on this casing when hot.Type: ApplicationFiled: April 21, 2009Publication date: May 26, 2011Applicant: SNECMAInventors: Caroline Jacqueline Denise Berdou, Sylvain Duval, Romain Nicolas Lunel
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Publication number: 20110113789Abstract: A gas turbine engine combustion chamber including at least one deflector mounted on the chamber end wall and including an opening for a carburetted air supply device. The deflector includes an opening, corresponding to the chamber end wall opening, with an annular cylindrical part for attachment to the wall, the cylindrical part including a mechanical attachment mechanism collaborating with a complementary attachment mechanism on a metal sleeve secured to the wall and a cylindrical centering cup fixed by one end to the sleeve and housed inside the cylindrical part of the deflector.Type: ApplicationFiled: June 10, 2009Publication date: May 19, 2011Applicant: SNECMAInventors: Sylvain Duval, Didier Hippolyte Hernandez, Romain Nicolas Lunel
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Patent number: 7909573Abstract: A casing cover for enclosing a casing in a jet engine is disclosed. The casing cover includes two coaxial shells arranged one inside the other and radial envelopes which connect the two coaxial shells. Radial arms of the casing extend inside the radial envelopes. The cover is fastened at its downstream end to a first element of the casing and axially abuts at its upstream end on a second element of the casing. In a free state, an axial dimension of the cover of less than the axial distance of the casing between the point where the first element of the casing is fastened to the downstream end of the cover and the point where the second element of the casing axially abuts the upstream end of the cover such that the cover is tensioned axially when it is mounted on and fastened to the casing.Type: GrantFiled: March 16, 2007Date of Patent: March 22, 2011Assignee: SNECMAInventors: Laurent Bernard Cameriano, Sylvain Duval, Eric Masson, Herve Bernard Plisson
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Publication number: 20100058765Abstract: A turbomachine combustion chamber including a substantially L-shaped fuel injector and means for mounting and fastening the injector in an orifice of the casing of the chamber, said means including an outer collar carried by the injector and a removable annular spacer surrounding the injector and designed to be interposed between the collar of the injector and the casing.Type: ApplicationFiled: August 20, 2009Publication date: March 11, 2010Applicant: SNECMAInventors: Sylvain Duval, Didier Hippolyte Hernandez, Romain Nicolas Lunel
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Patent number: 7673456Abstract: A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.Type: GrantFiled: June 12, 2008Date of Patent: March 9, 2010Assignee: SNECMAInventors: Laurent Bernard Cameriano, Michel Pierre Cazalens, Sylvain Duval, Romain Nicolas Lunel
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Publication number: 20100043449Abstract: Turbomachine comprising an annular combustion chamber (48) comprising two, a radially inner (24) and a radially outer (26), walls exhibiting symmetry of revolution, which are connected at their upstream ends by an annular chamber end wall (28) equipped with fuel-injection means, which turbomachine comprises suspension means (50) for suspending the upstream end of the combustion chamber (48) from an outer casing (18).Type: ApplicationFiled: July 22, 2008Publication date: February 25, 2010Applicant: SNECMAInventors: Patrice Andre COMMARET, Sylvain Duval, Didier Hippolyte Hernandez, Francois Jean-Claude Vuillemenot Yann
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Publication number: 20080307792Abstract: The invention relates to a turbomachine combustion chamber comprising an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems comprising pilot injectors alternating circumferentially with full-throttle injectors, and at least one air admission opening out into the upstream end of the combustion area in a substantially longitudinal direction. The outer wall has a plurality of pilot cavities extending between the two longitudinal ends of the outer wall and extending radially towards thereof, the pilot cavities being fed with air from outside the combustion chamber in a common substantially circumferential direction. Each pilot injector opens out radially into a pilot cavity, and each full-throttle injector opens out radially between two adjacent pilot cavities.Type: ApplicationFiled: June 12, 2008Publication date: December 18, 2008Applicant: SNECMAInventors: Laurent Bernard Cameriano, Michel Pierre Cazalens, Sylvain Duval, Romain Nicolas Lunel
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Publication number: 20070217911Abstract: Casing cover (10) in a jet engine, comprising two coaxial shells (36, 38) arranged one inside the other and joined fixedly by radial envelopes (40) inside which extend radial arms (26) of the casing, the cover being fastened at its downstream end to an element of the casing and bearing axially at its upstream end on another element of the casing, and the cover having, in the free state, an axial dimension (D) of less than the axial distance (L) between the points where its downstream end is fastened to the casing and the points where its upstream end bears axially on the casing, and being tensioned axially when it is mounted on and fastened to the casing.Type: ApplicationFiled: March 16, 2007Publication date: September 20, 2007Applicant: SNECMAInventors: Laurent Bernard Cameriano, Sylvain Duval, Eric Masson, Herve Bernard Plisson
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Publication number: 20060189220Abstract: A system for testing transceiver modules associated to different multi-source agreement standards, comprising a transceiver testing device and an interface connection unit. The transceiver testing device comprises a processor for performing at least one testing operation on an MSA transceiver module associated to a certain multi-source agreement standard. The interface connection unit is suitable for connecting the MSA transceiver module to the transceiver testing device. The transceiver module includes a certain type of electrical connector element. The interface connection unit comprises a first connector component and a second connector component. The first connector component is adapted for being removably connecting the interface connection unit to the transceiver testing device. The first connector component is different from the certain type of connector element of the MSA transceiver module.Type: ApplicationFiled: February 18, 2005Publication date: August 24, 2006Inventors: Sylvain Duval, Harold Lebrun, Allan Ezri
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Publication number: 20060086093Abstract: A variable-section nozzle for a turbomachine, the nozzle comprising a plurality of moving flaps mounted on the downstream end of an annular casing of the turbomachine, a moving flap control system comprising control levers each associated with a respective moving flap and at least one actuator for actuating the control levers, and a plurality of pairs of arms each forming a control lever support, the arms of each support being secured both to the casing and to a control lever, each pair of arms forming a control lever support being formed as a single piece.Type: ApplicationFiled: October 13, 2005Publication date: April 27, 2006Applicant: SNECMAInventors: Mathieu Dakowski, Sylvain Duval, Olivier Kreder, Romain Lunel, Emmanuel Mandet, Guillaume Sevi