Patents by Inventor Laurent Bernard Cameriano
Laurent Bernard Cameriano 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: 10458654Abstract: The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall (12) and the other an external wall (14), between which emerge fuel injectors (19) each engaged in centring means (36) which are moveable in the radial direction in support means (38), the chamber also comprising means (50, 68) of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal (12) or external (14) walls of revolution.Type: GrantFiled: December 17, 2014Date of Patent: October 29, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Brice Le Pannerer, Laurent Bernard Cameriano, Pierre-François Simon Paul Pireyre
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Patent number: 10337740Abstract: The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis (52) in supporting means intended for being attached to the bottom of an annular chamber (18). According to the invention, the centring means include at least two radially external tabs (54, 56) each inserted respectively in a circumferential recess (60, 64) of the supporting means, the device including circumferential abutment means (78, 80, 74, 76, 82, 86, 84, 88) of the radial tabs (54, 56) of the centring means in the circumferential recesses (60, 64), the circumferential abutment means being configured such as to enable a greater angular displacement of a first (54, 154) one of the radial tabs in a first circumferential recess (60) relative to a second (56, 156) one of the radial tabs in a second circumferential recess (64).Type: GrantFiled: December 8, 2014Date of Patent: July 2, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pierre-François Simon Paul Pireyre, Brice Le Pannerer, Laurent Bernard Cameriano
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Patent number: 10190946Abstract: A measuring comb for temperature and/or pressure and/or chemical composition of the gases flowing at the outlet of a turbine engine flow path, in which the flow path extends around an axis of revolution of the flow path, is provided. The measuring comb includes: a comb body with an elongated shape, intended to face the outlet of the flow path, the comb body including at least one measuring opening arranged along an axis, the measuring opening being configured to tap gases flowing at the outlet of the flow path; and an adjusting system configured to adjust an angle between the axis of the at least one measuring opening and the axis of revolution, so as to allow orientation of the at least one measuring opening in the flow direction of the gases at the outlet of the flow path.Type: GrantFiled: May 27, 2015Date of Patent: January 29, 2019Assignee: SAFRAN AIRCRAFTS ENGINESInventors: Romain Nicolas Lunel, Laurent Bernard Cameriano, Jeremy Giordan, Denis Jean Maurice Sandelis, Aurelien Lionel Tedesco
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Publication number: 20180163965Abstract: The invention relates to an annular combustion chamber in a turbine engine, comprising two coaxial walls of revolution, one an internal wall (12) and the other an external wall (14), between which emerge fuel injectors (19) each engaged in centring means (36) which are moveable in the radial direction in support means (38), the chamber also comprising means (50, 68) of axial retention in the upstream direction of the centring means. According to the invention, the means of axial retention in the upstream direction are removably fixed to at least one of the internal (12) or external (14) walls of revolution.Type: ApplicationFiled: December 17, 2014Publication date: June 14, 2018Applicant: SNECMAInventors: Brice Le Pannerer, Laurent Bernard Cameriano, Pierre-François Simon Paul Pireyre
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Patent number: 9897316Abstract: A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall.Type: GrantFiled: December 2, 2010Date of Patent: February 20, 2018Assignee: SNECMAInventors: Caroline Jacqueline Denise Berdou, Laurent Bernard Cameriano
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Publication number: 20170191901Abstract: A measuring comb for temperature and/or pressure and/or chemical composition of the gases flowing at the outlet of a turbine engine flow path, in which the flow path extends around an axis of revolution of the flow path, is provided. The measuring comb includes: a comb body with an elongated shape, intended to face the outlet of the flow path, the comb body including at least one measuring opening arranged along an axis, the measuring opening being configured to tap gases flowing at the outlet of the flow path; and an adjusting system configured to adjust an angle between the axis of the at least one measuring opening and the axis of revolution, so as to allow orientation of the at least one measuring opening in the flow direction of the gases at the outlet of the flow path.Type: ApplicationFiled: May 27, 2015Publication date: July 6, 2017Applicant: Safran Aircraft EnginesInventors: Romain Nicolas LUNEL, Laurent Bernard CAMERIANO, Jermey GIORDAN, Denis Jean Maurice SANDELIS, Aurelien Lionel TEDESCO
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Patent number: 9605594Abstract: A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section.Type: GrantFiled: January 25, 2012Date of Patent: March 28, 2017Assignee: SNECMAInventors: Thierry Cortes, Laurent Bernard Cameriano
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Publication number: 20170003028Abstract: The invention relates to a device for supporting and centring a fuel injector in a turbine engine combustion chamber, which includes means for centring a fuel injector along an axis, which are movable in a plane that is radial to the centring axis (52) in supporting means intended for being attached to the bottom of an annular chamber (18). According to the invention, the centring means include at least two radially external tabs (54, 56) each inserted respectively in a circumferential recess (60, 64) of the supporting means, the device including circumferential abutment means (78, 80, 74, 76, 82, 86, 84, 88) of the radial tabs (54, 56) of the centring means in the circumferential recesses (60, 64), the circumferential abutment means being configured such as to enable a greater angular displacement of a first (54, 154) one of the radial tabs in a first circumferential recess (60) relative to a second (56, 156) one of the radial tabs in a second circumferential recess (64).Type: ApplicationFiled: December 8, 2014Publication date: January 5, 2017Applicant: SnecmaInventors: Pierre-Francois Simon Paul PIREYER, Brice LE PANNERER, Laurent Bernard CAMERIANO
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Publication number: 20130291546Abstract: A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section.Type: ApplicationFiled: January 25, 2012Publication date: November 7, 2013Applicant: SNECMAInventors: Thierry Cortes, Laurent Bernard Cameriano
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Patent number: 8453459Abstract: A fuel injection system for an annular combustion chamber of a turbomachine including a support device for supporting and centering a fuel injector head; and a bowl arranged downstream from the support device and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface is disclosed. The upstream radial surface includes a device which disturbs the flow of cooling air and increases the heat exchange area between the air and the collar.Type: GrantFiled: February 22, 2011Date of Patent: June 4, 2013Assignee: SNECMAInventors: Laurent Bernard Cameriano, Christophe Pieussergues, Denis Jean Maurice Sandelis
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Publication number: 20120240584Abstract: A combustion chamber for a turbine engine such as an airplane turboprop or turbojet has inner and outer annular walls forming bodies of revolution that are connected together by an annular chamber end wall. The inner wall is constituted by a single thickness of material that presents thickness and/or nature varying along the longitudinal axis and/or the circumferential direction of said wall.Type: ApplicationFiled: December 2, 2010Publication date: September 27, 2012Applicant: SNECMAInventors: Caroline Jacqueline Denise Berdou, Laurent Bernard Cameriano
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Publication number: 20110203294Abstract: A fuel injection system for an annular combustion chamber of a turbomachine, the system comprising support means for supporting and centering a fuel injector head, and a bowl arranged downstream from the support means and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface, and including on said surface means for disturbing the flow of cooling air and for increasing the heat exchange area between the air and the collar.Type: ApplicationFiled: February 22, 2011Publication date: August 25, 2011Applicant: SNECMAInventors: Laurent Bernard CAMERIANO, Christophe Pieussergues, Denis Jean Maurice Sandelis
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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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Patent number: 7866162Abstract: An exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held by an elastically deformable element that acts axially.Type: GrantFiled: June 19, 2007Date of Patent: January 11, 2011Assignee: SnecmaInventors: Stephane Pierre Guillaume Blanchard, Laurent Bernard Cameriano, Mathieu Dakowski, Alain Pierre Page
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Patent number: 7673461Abstract: A structural turbine engine casing is disclosed. The casing includes a central hub, at least one intermediate shroud, and an external ring, which are concentric, the external ring and the intermediate shroud being connected via links, the intermediate shroud and the central hub being connected by a series of radially fastened hollow arms. The series of arms includes at least one main arm and at least one secondary arm, each main arm being arranged in the continuation of a link and having a mass which is greater than that of a secondary arm arranged at a distance from the links.Type: GrantFiled: September 13, 2006Date of Patent: March 9, 2010Assignee: SNECMAInventors: Laurent Bernard Cameriano, Nicolas Pierre-Marie Girard
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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: 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: 20080104941Abstract: Mounting an exhaust cone of composite material. The exhaust cone is mounted to extend an adapter ring and it is held in particular by elastic stress means that act axially.Type: ApplicationFiled: June 19, 2007Publication date: May 8, 2008Applicant: SNECMAInventors: Stephane Pierre Guillaume BLANCHARD, Laurent Bernard Cameriano, Mathieu Dakowski, Alain Pierre Page
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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