Patents by Inventor Georges Mazeaud
Georges Mazeaud 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: 7805949Abstract: A device for supporting and housing auxiliaries in a bypass turbojet is disclosed. The device includes two coaxial case rings arranged one inside the other and connected by tubular radial arms through which fluid ducts and electric cables pass. At least one of the radial arms includes on a lateral face a detachable panel whose removal allows access to turbojet equipment situated radially inside the internal case ring in alignment with the radial arm.Type: GrantFiled: June 28, 2006Date of Patent: October 5, 2010Assignee: SNECMAInventors: Georges Mazeaud, Didier Jean-Louis Yvon
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Patent number: 7543442Abstract: A turbofan jet engine includes an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct. At least one removable modular arm forming a connection for ancillaries is arranged between the outer fan duct and the inner fan duct. The removable arm provides a connection of ancillaries outside the outer fan duct to ancillaries inside the inner fan duct.Type: GrantFiled: January 10, 2005Date of Patent: June 9, 2009Assignee: SnecmaInventors: Jacky Derenes, Georges Mazeaud
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Patent number: 7506499Abstract: A turbofan jet engine includes an outer casing supported by arms, an inner casing facing the outer casing, ancillaries, and an ancillaries distribution support. The ancillaries distribution support is formed along the axis of an arm on the inner casing. The ancillaries distribution support includes a first sole plate for reception of ancillaries on the outer side of the inner casing and a second sole plate for reception of ancillaries on the inner side of the inner casing. Such a turbofan jet engine reduces the longitudinal dimension necessary for the ancillaries to pass through.Type: GrantFiled: January 10, 2005Date of Patent: March 24, 2009Assignee: SnecmaInventors: Jeremy Fert, Georges Mazeaud
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Patent number: 7461813Abstract: An air intake layout for a turboprop. A nacelle surrounding an intake section of the turboprop behind the fan propeller can be moved away from the main part of the nacelle and can be divided into two parts that may be extracted so as to leave full access to the panel leading to equipment in a central compartment, whereas the panel was partially covered by the air intake leading edge.Type: GrantFiled: April 28, 2003Date of Patent: December 9, 2008Assignee: SnecmaInventors: Michel Chaumeret, Georges Mazeaud
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Publication number: 20070084216Abstract: A device for supporting and housing auxiliaries in a bypass turbojet, comprising two coaxial case rings arranged one inside the other and connected by tubular radial arms through which fluid ducts and electric cables pass, at least one of the radial arms comprising on a lateral face a detachable panel whose removal allows access to turbojet equipment situated radially inside the internal case ring in alignment with the radial arm.Type: ApplicationFiled: June 28, 2006Publication date: April 19, 2007Applicant: SNECMAInventors: Georges MAZEAUD, Didier Yvon
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Publication number: 20070063097Abstract: An air intake layout for a turboprop. A nacelle surrounding an intake section of the turboprop behind the fan propeller can be moved away from the main part of the nacelle and can be divided into two parts that may be extracted so as to leave full access to the panel leading to equipment in a central compartment, whereas the panel was partially covered by the air intake leading edge.Type: ApplicationFiled: April 28, 2003Publication date: March 22, 2007Applicant: SNECMA MOTEURSInventors: Michel Chaumeret, Georges Mazeaud
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Patent number: 7100869Abstract: The carrier structure of the invention is used for carrying a turboprop and it is designed to be mounted beneath and/or in front of an airplane wing. In characteristic manner, the carrier structure comprises: a top portion comprising a front arch, a rear arch, and longitudinal beams; an upwardly-open removable bottom portion comprising at least two bottom arches and longerons; the bottom portion being demountably fixed to the top portion by centering and fixing devices, the bottom and top portions together defining a housing suitable for receiving said turboprop, and a suspension for carrying said turboprop.Type: GrantFiled: February 19, 2004Date of Patent: September 5, 2006Assignee: SNECMA MoteursInventors: Jean-Louis Picard, Georges Mazeaud
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Patent number: 7007890Abstract: The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.Type: GrantFiled: November 12, 2004Date of Patent: March 7, 2006Assignee: Snecma MoteursInventors: Bruno Beutin, Didier Yvon, Georges Mazeaud, Fabien Burdin
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Publication number: 20050247042Abstract: This invention concerns a turbofan jet engine comprising an outer casing supported by arms, an inner casing facing the casing and ancillaries. An ancillaries distribution support is formed along the axis of an arm, on the inner casing, comprising a first sole plate for reception of ancillaries on the outer side of the inner casing. The invention reduces the longitudinal dimension necessary for the ancillaries to pass through.Type: ApplicationFiled: January 10, 2005Publication date: November 10, 2005Applicant: SNECMA MOTEURSInventors: Jeremy Fert, Georges Mazeaud
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Publication number: 20050247043Abstract: The present invention concerns a turbofan jet engine comprising an outer fan duct, an inner fan duct, fluid-conveying ancillaries located outside the outer fan duct, fluid-conveying ancillaries located inside the inner fan duct, characterized by the fact that at least one removable modular arm forming a connection for ancillaries is arranged between the outer fan duct and the inner fan duct. With the invention, the connection of ancillaries outside the outer fan duct to ancillaries inside the inner fan duct is achieved simply by means of a removable arm that is easy to mount and dismount.Type: ApplicationFiled: January 10, 2005Publication date: November 10, 2005Applicant: SNECMA MOTEURSInventors: Jacky Derenes, Georges Mazeaud
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Publication number: 20050178887Abstract: The turbojet according to the invention is designed to be fixed onto the upper part of the aft section of the fuselage of an aircraft using at least one coat hanger, the turbojet comprising a fan, a forward casing, an aft casing, accessories arranged around the periphery of the forward casing, the forward casing comprising attachment points, for the coat hanger. The attachment points are arranged so that the turbojet can be installed indifferently on either side of the aircraft fuselage, accessories being arranged on the casing so that they are accessible from the outside of the fuselage regardless of which side the installation is done.Type: ApplicationFiled: November 12, 2004Publication date: August 18, 2005Applicant: SNECMA MOTEURSInventors: Bruno Beutin, Didier Yvon, Georges Mazeaud, Fabien Burdin
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Publication number: 20050150970Abstract: The cooling system (30) for an aircraft engine (10) comprises a channel (32) that draws off cold air in the secondary air flow (200), and a heat exchanger (34) located in the channel (32) and in which hot air circulates. The channel (32) comprises: a supply pipe (322) and an evacuation pipe (326) fixed to the nacelle (324), an intermediate box (324) located between the supply pipe (322) and the evacuation pipe (326), fixed to the engine (10), and in which the heat exchanger (34) is placed. Application to cooling of hot parts (22) in an aircraft engine (10).Type: ApplicationFiled: December 8, 2004Publication date: July 14, 2005Applicant: SNECMA MOTEURSInventors: Bruno Beutin, Georges Mazeaud, Laurent Palmisano, Vincent Fonquerne, Didier Yvon
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Publication number: 20040227033Abstract: The carrier structure of the invention is used for carrying a turboprop and it is designed to be mounted beneath and/or in front of an airplane wing.Type: ApplicationFiled: February 19, 2004Publication date: November 18, 2004Applicant: SNECMA MOTEURSInventors: Jean-Louis Picard, Georges Mazeaud
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Patent number: 6474596Abstract: A suspension system for an aircraft powerplant attached to an aircraft frame and having a housing. The suspension system includes a spindle mounted in a spindle support rigidly joined to the aircraft frame, a bearing cage affixed to the housing and having a bearing positioned therein, a pair of suspension arms connected to the spindle support, and a pair of lateral linkrods configured to link the housing and the suspension arms. The side surfaces of the bearing cage and the suspension arms define a clearance therebetween concentric to the Y-axis. The bearing cage is configurable along the spindle such that the bearing cage is limited to displacement relative to the longitude of the spindle while maintaining contact with the spindle.Type: GrantFiled: October 3, 2000Date of Patent: November 5, 2002Assignee: SNECMA MoteursInventors: Antoine Emmanuel Cousin, Georges Mazeaud, Jean-Louis Picard
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Patent number: 6129509Abstract: The particle trap (15) that extends behind an elbow in the air flow stream (6) in a turbo-prop engine is delimited at the back by an end plate (12) to which intake housing suspension rods (10) supporting the front of the rotating shaft (2), are fastened. It is divided by suspension arms (11) which may be drilled (21) to restore the continuity of the annular chamber forming the trap. Therefore the intake housing suspension device extends through the trap. This type of trap makes use of the inertia of solid bodies carried by the air drawn in, and which could damage the engine blades, and to collect them.Type: GrantFiled: June 29, 1999Date of Patent: October 10, 2000Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "Snecma"Inventors: Antoine Emmanuel Cousin, Georges Mazeaud
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Patent number: 5806793Abstract: A cooling device for an aircraft turboshaft engine includes a boundary layer suction device formed by a perforated external wall portion of the aircraft, a collector on the inside of the wall portion for receiving the air flowing in through the perforations, and a discharge device discharging the air from the collector. The cooling device is completed by a heat exchanger which is disposed in the path of the air flow through the collector, a pump for pumping fluid to be cooled through the heat exchanger from a circuit of the engine, and a regulator regulating the fluid flow through the exchanger to control the temperature of the fluid. The fluid which is cooled may be from the lubrication circuit, the fuel circuit, or an air circuit of the engine, and the boundary layer suction device is preferably disposed in the pod of the engine.Type: GrantFiled: December 12, 1996Date of Patent: September 15, 1998Assignee: Societe Nationale D'Etude Et De Construction De Moteurs D'Aviation "Snecma"Inventors: Pascal Noel Brossier, Georges Mazeaud, Jean-Marie Noel Pincemin
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Patent number: 5524430Abstract: A combustion chamber for a gas-turbine engine is disclosed in which the walls defining the combustion chamber may be easily attached to and removed from the engine structure. A dome member is attached to the engine structure such that it partially encloses the fuel injector nozzle in an upstream direction. The shape of the dome-member is such that it splits the incoming oxidizer flow into inner and outer flows which pass along the inner and outer sides of the combustion chamber. The inner and outer walls of the combustion chamber may be attached to an upstream end wall of the combustion chamber such that this assembly is removable as a unit from the dome member. The inner and outer walls, as well as the end wall, are releasably attached to the dome member such that the assembly can be removed from the gas-turbine engine without the necessity of removing or displacing the fuel injector nozzles or the dome member.Type: GrantFiled: January 14, 1993Date of Patent: June 11, 1996Assignee: Societe National D'Etude et de Construction de Moteurs D'Aviation S.N.E.C.M.A.Inventors: Georges Mazeaud, Christophe Pieussergues, Denis J. M. Sandelis
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Patent number: 5410870Abstract: Aircraft engine, whose ancillary equipment forms a unitary assembly wherein the equipment is located to the rear of the air intake duct in a substantially closed central compartment just upstream of the gas generator. The equipment positioned along the engine axis, which, inter alia, leads to low engine drag in operation.Type: GrantFiled: November 29, 1993Date of Patent: May 2, 1995Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation "SNECMA"Inventors: Michel G. R. Brault, Georges Mazeaud, Jean-Marie N. Pincemin, Pascal C. Wurniesky
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Patent number: 5347807Abstract: A jet engine includes a gas turbine, peripheral ramjet channels located oide the gas turbine and including burners wherein a gas circulation stream in the engine is subdivided over part of its length into a central turbojet stream which flows through the gas turbine, the peripheral ramjet channels and peripheral discharge channels terminating by flowing into a part of the gas circulation stream downstream of the turbine. A plurality of flaps are provided for opening and closing the central stream. A ring surrounds the central stream and extends in front of part of the peripheral discharge channels and ramjet channels. A motor is also provided for rotating the ring wherein the ring has a plurality of slots formed therein, the channels being arranged such that the slots successfully pass, during rotation of the ring in a continuous direction, in front of the discharge channels only, then in front of none of the channels and then in front of the ramjet channels only.Type: GrantFiled: June 14, 1993Date of Patent: September 20, 1994Assignee: Societe Nationale D'Etude et de Construction de Moteurs d'Aviaton "SNECMA"Inventors: Pascal N. Brossier, Georges Mazeaud, Pascal C. Wurniesky
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Patent number: 5343695Abstract: A jet engine has a central turbojet stream and a peripheral ram jet stream which can be in turn obstructed or freed by flaps. The flaps can be opened outwardly and are located on an intake cone and at an inlet of the peripheral stream. The operation of the flaps is a function of the sought operating mode. This arrangement permits a very good guidance of gases.Type: GrantFiled: June 14, 1993Date of Patent: September 6, 1994Assignee: Societe Nationale d'Etude Et de Construction de Moteurs d'Aviation "SNECMA"Inventors: Noel B. Pascal, Georges Mazeaud, Claude W. Pascal