Patents by Inventor Marc Marchi
Marc Marchi 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: 7591594Abstract: A turbomachine roller bearing that supports a shaft constituted by a trunnion of a shaft line of a high-pressure spool of a turbomachine to rotate relative to a stationary support that is connected to a casing of the turbomachine, said bearing comprising rollers inserted between an outer ring disposed adjacent to the stationary support and an inner ring disposed adjacent to the high-pressure trunnion, the inner ring extending along the axis beyond a downstream end of the high-pressure trunnion to which it is secured by clamping means, and being provided with anti-rotation means for preventing said inner ring from rotating relative to the high-pressure trunnion.Type: GrantFiled: March 7, 2005Date of Patent: September 22, 2009Assignee: SNECMAInventors: Gilles Charier, Guy Dusserre-Telmon, Marc Marchi, Jean-Pierre Mourlan, Patrice Rosset, Zoltan Zsiga
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Patent number: 7556474Abstract: A turbomachine including a wheel with hollow blades that are cooled internally by a forced flow of cooling air. According to an important characteristic of the invention, a hook-annulus (70) is interposed between the outer edge of the labyrinth-disk (52) and the rotor disk (36), the hook-annulus including a retaining shoulder (72) constituting an outer annular hook in which the outer edge of the labyrinth-disk is engaged, and a bearing shoulder (74) constituting an inner hook engaged in a groove around the circumference of the rotor disk.Type: GrantFiled: March 2, 2005Date of Patent: July 7, 2009Assignee: SnecmaInventor: Marc Marchi
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Patent number: 7513740Abstract: A turbine ring made up of an assembly of a plurality of sectors forming the outer shroud of the rotor of said turbine. The sectors are united end to end with interposed sealing systems comprising tongues housed in slots, said tongues being rectilinear and engaged in respective rectilinear slots in the radial faces of said sectors.Type: GrantFiled: April 12, 2005Date of Patent: April 7, 2009Assignee: SNECMAInventors: Nicolas Hervy, Marc Marchi, Ludovic Nicollas
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Publication number: 20090074579Abstract: A turbine ring made up of an assembly of a plurality of sectors forming the outer shroud of the rotor of said turbine. The sectors are united end to end with interposed sealing systems comprising tongues housed in slots, said tongues being rectilinear and engaged in respective rectilinear slots in the radial faces of said sectors.Type: ApplicationFiled: April 12, 2005Publication date: March 19, 2009Applicant: SNECMA MOTEURSInventors: Nicolas Hervy, Marc Marchi, Ludovic Nicollas
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Patent number: 7217100Abstract: A device for holding an annular end plate against a radial face of a rotor disc, the disc having in the radial face an annular recess behind a collar extending radially outwards, and the end plate having, in its radially inner part, an annular base bearing against the radially outer wall of the recess and a foot extending radially inwards in the recess from the base, the device including a split annular retaining ring disposed in the recess. The ring is constituted by a snap ring interposed axially between the foot of the end plate and the collar and the peripheral surface of which butts against the base, the peripheral surface and the collar comprising, when joined, notches, which open radially outwards and are intended to receive compression tools for the snap ring, which tools retract into the contour of the collar during the assembly or disassembly of the end plate.Type: GrantFiled: July 19, 2004Date of Patent: May 15, 2007Assignee: Snecma MoteursInventors: Kamel Benderradji, Marc Marchi
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Patent number: 7214034Abstract: A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.Type: GrantFiled: May 28, 2003Date of Patent: May 8, 2007Assignee: Snecma MoteursInventors: Chantal Giot, Marc Marchi, Christian Gosselin, Eric Bil
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Patent number: 7140840Abstract: A turboshaft engine, such as for example a turbine, including a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and includes a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.Type: GrantFiled: September 22, 2004Date of Patent: November 28, 2006Assignee: Snecma MoteursInventors: Jean-Claude Taillant, Marc Marchi
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Publication number: 20060245924Abstract: The gastight sealing device associated with a functional clearance (20) existing between two sectors of a turbomachine comprises an annular plate (100) wound up on itself over at least one turn, covering said functional clearance (20).Type: ApplicationFiled: April 25, 2006Publication date: November 2, 2006Applicant: SNECMAInventors: David Audeon, Kamel Benderradji, Marc Marchi
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Patent number: 7037071Abstract: The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip (30) disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover (31) disposed between said strips, and by a holding member for holding said strips in the sealing position.Type: GrantFiled: September 18, 2002Date of Patent: May 2, 2006Assignee: Snecma MoteursInventors: Serge Louis Antunes, Patrick Pierre Bernard Gazeau, Marc Marchi, Patrice Jean Marc Rosset
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Patent number: 7011493Abstract: A turbomachine includes a casing, a rotor, and a plurality of cooled ring segments installed between the casing and the rotor, each ring segment containing a main cooling cavity and being attached to the casing by a fastening device. The fastening device can include a clamping screw positioned more or less radially and pinning the ring segment against the casing. The clamping screw is crossed through by a cooling airway that communicates with the main cooling cavity of the ring segment.Type: GrantFiled: March 2, 2004Date of Patent: March 14, 2006Assignee: Snecma MoteursInventors: Marc Marchi, Paul Rodrigues, Patrice Rosset, Jean-Claude Taillant, Jean-Baptiste Arilla
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Publication number: 20050249590Abstract: A turbomachine including a wheel with hollow blades that are cooled internally by a forced flow of cooling air. According to an important characteristic of the invention, a hook-annulus (70) is interposed between the outer edge of the labyrinth-disk (52) and the rotor disk (36), the hook-annulus including a retaining shoulder (72) constituting an outer annular hook in which the outer edge of the labyrinth-disk is engaged, and a bearing shoulder (74) constituting an inner hook engaged in a groove around the circumference of the rotor disk.Type: ApplicationFiled: March 2, 2005Publication date: November 10, 2005Applicant: SNECMA MOTEURSInventor: Marc Marchi
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Publication number: 20050196088Abstract: A turbomachine roller bearing that supports a shaft constituted by a trunnion of a shaft line of a high-pressure spool of a turbomachine to rotate relative to a stationary support that is connected to a casing of the turbomachine, said bearing comprising rollers inserted between an outer ring disposed adjacent to the stationary support and an inner ring disposed adjacent to the high-pressure trunnion, the inner ring extending along the axis beyond a downstream end of the high-pressure trunnion to which it is secured by clamping means, and being provided with anti-rotation means for preventing said inner ring from rotating relative to the high-pressure trunnion.Type: ApplicationFiled: March 7, 2005Publication date: September 8, 2005Applicant: Snecma MoteursInventors: Gilles Charier, Guy Dusserre-Telmon, Marc Marchi, Jean-Pierre Mourlan, Patrice Rosset, Zoltan Zsiga
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Publication number: 20050175463Abstract: A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.Type: ApplicationFiled: May 28, 2003Publication date: August 11, 2005Applicant: Snecma MoteursInventors: Chantal Giot, Marc Marchi, Christian Gosselin, Eric Bil
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Publication number: 20050095123Abstract: Turboshaft engine, such as for example a turbine, comprising a segmented seal between two longitudinally adjacent elements such as, for example, a casing and a ring of sectors of vanes. According to one embodiment, a seal is interposed between a casing and a ring of sectors of vanes and consists of a plurality of flexible segments having a straight deformation zone and a straight fluid-tight bearing zone.Type: ApplicationFiled: September 22, 2004Publication date: May 5, 2005Applicant: SNECMA MOTEURSInventors: Jean-Claude Taillant, Marc Marchi
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Publication number: 20050042108Abstract: The invention relates to a device for holding an annular end plate (5) against a radial face (4) of a rotor disc (1), the said disc having in the said radial face an annular recess (7) behind a collar (13) extending radially outwards, and the said end plate (5) having, in its radially inner part, an annular base bearing against the radially outer wall of the recess (7) and a foot extending radially inwards in the recess (7) from the base, the said device comprising a split annular retaining ring disposed in the recess (7).Type: ApplicationFiled: July 19, 2004Publication date: February 24, 2005Applicant: SNECMA MOTEURSInventors: Kamel Benderradji, Marc Marchi
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Publication number: 20040239050Abstract: The invention provides a device for holding strip sealing gaskets on a turbomachine nozzle, the nozzle being constituted by a plurality of sectors having guide vanes which extend between inner and outer platforms elements, at least one of said platform elements having a sealing strip (30) disposed radially in a space between said platform element and an adjacent structural element in order to provide fluid tightness between said elements, the corresponding strips of two adjacent sectors touching, and their joint being covered by a joint cover (31) disposed between said strips, and by a holding member for holding said strips in the sealing position.Type: ApplicationFiled: March 17, 2004Publication date: December 2, 2004Inventors: Serge Louis Antunes, Patrick Pierre Bernard Gazeau, Marc Marchi, Patrice Jean Marc Rosset
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Publication number: 20040219009Abstract: The invention concerns a turbomachine (100) comprising a casing (102), a rotor (4), and a plurality of cooled ring segments (108) installed between the casing and the rotor, each ring segment containing a main cooling cavity (162) and being attached to the casing by means of a fastening device (132). According to the invention, the fastening device (132) comprises a clamping screw (134) positioned more or less radially and pinning the ring segment against the casing. The clamping screw (134) is crossed through by a cooling airway (174) that communicates with the main cooling cavity (162) of the ring segment.Type: ApplicationFiled: March 2, 2004Publication date: November 4, 2004Applicant: SNECMA MOTEURSInventors: Marc Marchi, Paul Rodrigues, Patrice Rosset, Jean-Claude Taillant, Jean-Baptiste Arilla
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Patent number: 5915919Abstract: Layout for adjusting the diameter of a turbine engine ring (5) positioned facing mobile rotor blades (4) and connected to a case element (7). The latter is provided with a cavity (16) communicating with chambers (21, 23) around a gas flow stream (31). A limited air current traverses the cavity (16) and is sufficiently reduced to ensure the development of a heat convection, which renders uniform the temperature of the case element (7) and the ring (5) and consequently the diameter of the latter.Type: GrantFiled: July 11, 1997Date of Patent: June 29, 1999Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"Inventors: Jean-Claude Taillant, Laurent Palmisano, Marc Marchi, Patrick Rossi