Patents by Inventor Bruno Beutin
Bruno Beutin 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: 11866183Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.Type: GrantFiled: April 15, 2022Date of Patent: January 9, 2024Assignees: Safran Nacelles, Safran Aircraft Engines, INSTITUT SUPERIEUR DE L'AÉRONAUTIQUE ET DE L'ESPACEInventors: Patrick Gonidec, Miguel Angel Aguirre, Nicolas Tantot, Bruno Beutin, Bernard Robic, Sébastien Duplaa
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Patent number: 11834187Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.Type: GrantFiled: August 20, 2020Date of Patent: December 5, 2023Assignees: Safran Nacelles, Safran Aircraft EnginesInventors: Patrick Boileau, Bruno Beutin
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Publication number: 20220242583Abstract: An aircraft includes a fuselage carrying a nacelle of the aircraft offset relative to a wing of the aircraft. The nacelle forms an air inlet fairing of a propulsion assembly. The nacelle includes a lower wall and an upper wall delimiting together a height of the nacelle. The lower wall includes an air inlet edge being contiguous with a trailing edge of the wing.Type: ApplicationFiled: April 15, 2022Publication date: August 4, 2022Applicants: Safran Nacelles, SAFRAN AIRCRAFT ENGINES, INSTITUT SUPERIEUR DE L'AERONAUTIQUE ET DE L'ESPACEInventors: Patrick Gonidec, Miguel Angel Aguirre, Nicolas Tantot, Bruno Beutin, Bernard Robic, Sébastien Duplaa
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Publication number: 20200377221Abstract: A drive unit includes an engine such as a turbofan engine and a nacelle which includes, on the outside around an annular stream of fresh air, starting from upstream, an air inlet, front side covers, a thrust reverser having reversal gratings and movable rear covers. The front side covers surround the reversal gratings of the thrust reverser when it is closed, and the movable rear covers retreat with said gratings to open the reverser. The engine includes lifting points that form heavy-duty attachment points intended to receive handling clevis for lifting and transporting the drive unit. The lifting points are two upper lifting points arranged on the engine, each on one side of the engine radially behind the front side covers above the horizontal diameter (D) of the drive unit.Type: ApplicationFiled: August 20, 2020Publication date: December 3, 2020Applicants: Safran Nacelles, Safran Aircraft EnginesInventors: Patrick BOILEAU, Bruno BEUTIN
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Patent number: 9957056Abstract: The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.Type: GrantFiled: May 20, 2015Date of Patent: May 1, 2018Assignees: AIRCELLE, SNECMAInventors: Patrick Boileau, Pierre Caruel, Carmen Ancuta, Bruno Beutin
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Publication number: 20150367946Abstract: The present disclosure relates to a propulsion unit for an aircraft including a nacelle which surrounds a turbojet engine. The nacelle has an inner structure surrounding a downstream compartment of the turbojet engine, and the inner structure includes two annular half-portions. The propulsion unit also includes a rail/guide unit and to move the annular half-portions between a working position and a maintenance position. In particular, the rail/guide unit radially moves away the annular half-portions relative to a longitudinal axis of the nacelle, during a translation movement of the annular half-portions. The nacelle is provided with a connecting rod which is connected to the annular half-portions and to the turbojet engine and so that the connecting rod contributes to rotate the annular half-portions about the rail.Type: ApplicationFiled: May 20, 2015Publication date: December 24, 2015Inventors: Patrick BOILEAU, Pierre Caruel, Carmen Ancuta, Bruno Beutin
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Patent number: 7950218Abstract: The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine so as to define a cold stream flow channel, the nacelle having an upstream end surrounding the fan of the engine and a stationary downstream end forming a gas exhaust nozzle, the nozzle having a throat section that corresponds to its smallest cross-section. The turbomachine further comprises means for taking in air from the cold stream flow channel upstream from the nozzle throat section, and means for injecting the taken-in air downstream from the nozzle throat section so as to open the throat section artificially.Type: GrantFiled: July 19, 2007Date of Patent: May 31, 2011Assignee: SNECMAInventors: Albert Bruno Beutin, Eric Landre
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Patent number: 7430852Abstract: A turbojet comprises at least a fan, a compressor, a combustion chamber, a turbine, and a rigid substantially-cylindrical jacket fastened at its upstream end to an intermediate casing and at its downstream end to an exhaust casing, the jacket serving to transmit forces between the intermediate casing and the exhaust casing.Type: GrantFiled: January 26, 2005Date of Patent: October 7, 2008Assignee: SNECMAInventors: Bruno Beutin, Nelson Dos Santos, Jeremy Fert, Fabienne Lacorre, Jean-Louis Picard
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Patent number: 7412819Abstract: A turbojet has a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. The compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.Type: GrantFiled: January 26, 2005Date of Patent: August 19, 2008Assignee: SNECMAInventors: Jacques Bart, Bruno Beutin, Yann Lebret
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Publication number: 20080141656Abstract: The invention relates to a bypass turbomachine comprising a gas turbine engine provided with a fan disposed on a longitudinal axis of the turbomachine, and an annular nacelle surrounding the engine so as to define a cold stream flow channel, the nacelle having an upstream end surrounding the fan of the engine and a stationary downstream end forming a gas exhaust nozzle, the nozzle having a throat section that corresponds to its smallest cross-section. The turbomachine further comprises means for taking in air from the cold stream flow channel upstream from the nozzle throat section, and means for injecting the taken-in air downstream from the nozzle throat section so as to open the throat section artificially.Type: ApplicationFiled: July 19, 2007Publication date: June 19, 2008Applicant: SNECMAInventors: Albert Bruno Beutin, Eric Landre
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Patent number: 7351174Abstract: The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.Type: GrantFiled: January 18, 2006Date of Patent: April 1, 2008Assignee: SNECMAInventors: Bruno Beutin, Jeremy Fert
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Publication number: 20080072572Abstract: Turbomachine fan duct comprising two coaxial cylindrical walls (60, 68), these being an internal wall and an external wall, respectively, the internal wall (68) consisting of a framework (70) to which panels (72) are removably attached, and the external wall (60) consisting of a single support structure (62) comprising openings (64) closed by removable panels (66), the openings (64) in the external wall having dimensions that allow the panels (72) of the internal wall to pass and allow these panels to be fitted onto and removed from the framework (70) of the internal wall.Type: ApplicationFiled: September 17, 2007Publication date: March 27, 2008Applicant: SNECMAInventors: Bruno BEUTIN, Jacky Derenes
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Publication number: 20070084191Abstract: The invention relates to thrust reversers comprising at least one mobile element (3), at least one locking device (7) comprising a hook (8) cooperating with a hookable part (6) in order to keep the mobile element (3) in the closed position, and a double detection system (10) detecting closure and locking comprising a sensor (15) for indicating, in particular by a signal, if the mobile element (3) is in the closed position and if the device (7) is in a locked position. According to the invention, the double detection system detecting closure and locking of a mobile element of a turbojet thrust reverser comprises a means (16) of detection of the hookable part (6) and of activation of a second means (17) of detection of the crooked end (13) of the hook (8).Type: ApplicationFiled: June 26, 2006Publication date: April 19, 2007Applicant: SNECMAInventors: Bruno BEUTIN, Marc TESNIERE
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Publication number: 20060277920Abstract: The invention relates to a twin spool turbine engine comprising a high-pressure rotor and a low-pressure rotor, at least one accessory gearbox, a drive means, driving coaxial transmission shafts that transmit movement to the accessory gearbox, characterized in that the drive means comprises a high-pressure drive pinion secured to the high-pressure rotor near its upstream end, a low-pressure drive pinion secured to the low-pressure rotor upstream of the high-pressure rotor, and a power take-off module in direct mesh with the drive pinions, driving the transmission shafts. By virtue of the invention, the transmission shafts run coaxial with one another and therefore pass through a single arm. The use of a power take-off module simplifies the mechanism. The turbine engine is simpler to assemble.Type: ApplicationFiled: February 9, 2006Publication date: December 14, 2006Applicant: SNECMAInventors: Jacques BART, Bruno BEUTIN, Patrick Charles MOREL
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Publication number: 20060230744Abstract: Exhaust nozzle 14 for an engine of a flying craft, comprising a tubular body with two outlet ducts 16, 18 and boxes 26, 28 for injecting gas into the outlet ducts for the purpose of thrust vectoring, these boxes having windows 38 aligned with slots 39 formed in the outlet ducts, and controlled means for adjusting the outflow of gas injected into the outlet ducts.Type: ApplicationFiled: April 13, 2006Publication date: October 19, 2006Applicant: SNECMAInventors: Bruno Beutin, Jeremy Fert
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Publication number: 20060226282Abstract: Deflection system for a gas stream 11 in an exhaust nozzle 10 of a flying craft, comprising fixed structural housings 18,20 which extend perpendicularly to the gas stream 11 and which are fed with deflection gas through one of their ends external to the nozzle 10, these housings 18,20 containing in their side walls 22,28 gas injection slits 23,30 oriented in oblique directions 24,26 relative to the gas stream 11, and controlled means for the adjustable closure of these slits 23,30.Type: ApplicationFiled: March 23, 2006Publication date: October 12, 2006Applicant: SNECMAInventors: Bruno Beutin, Jeremy Fert
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Patent number: 7097415Abstract: A low-pressure turbine of a turbomachine, the turbomachine comprising a high-pressure turbine disposed upstream from the low-pressure turbine, and an exhaust casing disposed downstream from the low-pressure turbine, the low-pressure turbine comprising a rotor secured on a low-pressure trunnion, a low-pressure shaft, a first rolling bearing disposed on said low-pressure shaft and supporting a high-pressure trunnion having fastened thereon a rotor of the high-pressure turbine, a second rolling bearing disposed on said low-pressure trunnion downstream from said first rolling bearing and enabling said low-pressure trunnion to be centered relative to said exhaust casing, and a system of fluting for enabling said low-pressure trunnion to drive said low-pressure shaft, said system of fluting being disposed between said first and second rolling bearings.Type: GrantFiled: August 4, 2004Date of Patent: August 29, 2006Assignee: Snecma MoteursInventors: Jacques Bart, Bruno Beutin, Philippe Bouiller
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Publication number: 20060183593Abstract: The twin turbo-shaft engine according to the invention comprises a high pressure rotor and a low pressure rotor, at least one accessory gearbox driven by mechanical transmission means, main drive pinion means, on each rotor, driving power transmission means each associated with an input to a differential, the output of which drives a drive shaft of the accessory gearbox. It is characterised by the fact that the power transmission means extend in two different structural arms, the power transmission means of one of the rotors being connected to a power transfer box fulfilling two functions, firstly transmission of power to an input to the differential, and secondly modification of the transmission speed. The required space in each arm is thus reduced and the efficiency of the accessory gearbox is high.Type: ApplicationFiled: January 18, 2006Publication date: August 17, 2006Applicant: SNECMAInventors: Bruno Beutin, Jeremy Fert
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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: 20050198941Abstract: The invention relates to a turbojet having a low-pressure compressor and two fans at the front of an intermediate casing which fans are driven by two independent shafts. Said compressor is disposed under the rear fan and has a downstream ring of rotor blades connecting the rear fan to the drive shaft of the rear fan, an upstream rotor blade ring that is connected to the drive shaft of the front fan and at least one ring of stator blades that is disposed between the rings of rotor blades and inside an outer stator that is supported by a second intermediate casing. Bearings are interposed respectively between the two intermediate casings and the two shafts.Type: ApplicationFiled: January 26, 2005Publication date: September 15, 2005Applicant: SNECMA MOTEURSInventors: Jacques Bart, Bruno Beutin, Yann Lebret