Patents by Inventor Michel Brault
Michel Brault 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: 10539031Abstract: A turbine engine impeller including a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc. The root of each vane is connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades. The impeller further includes two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes.Type: GrantFiled: December 10, 2015Date of Patent: January 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jean-Philippe Antoine Beaujard, Roland Gilbert Michel Brault, Nathalie Nowakowski
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Patent number: 10473035Abstract: The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), said power transmission shaft being driven via the speed reduction gear (7) by a turbine shaft (2) secured to one (C) of said coaxial modules that is separate from the first module, the speed reduction gear comprising a drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low-pressure compressor rotor (1 a), characterized in that it comprises a first nut (16) for fastening the drive means to the journal and a second nut (14) for fastening the drive means to the turbine shaft.Type: GrantFiled: November 6, 2014Date of Patent: November 12, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Roland Gilbert Michel Brault, Nathalie Nowakowski
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Publication number: 20180328288Abstract: A front part of an aircraft turbomachine of the bypass type including a single fan, a gas generator positioned downstream of the fan, a reducer interposed between the gas generator and the fan, a flow splitter and a structure with structural outlet guide vanes. The vanes each have a root arranged upstream of the flow splitter and the reducer is also arranged at least half upstream of the flow splitter.Type: ApplicationFiled: November 14, 2016Publication date: November 15, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Kevin Morgane LEMARCHAND, Michel BRAULT, Guillaume Olivier Vartan MARTIN
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Publication number: 20160298548Abstract: The present invention relates to an engine (1) with a modular structure comprising a plurality of coaxial modules (A, B, C) with, at one end, a first module (A) comprising a power transmission shaft (3) and a speed reduction gear (7), said power transmission shaft being driven via the speed reduction gear (7) by a turbine shaft (2) secured to one (C) of said coaxial modules that is separate from the first module, the speed reduction gear comprising a drive means (8 and 9) fixed to the turbine shaft (2) and to a journal (13) of a shaft of a low-pressure compressor rotor (1a), characterized in that it comprises a first nut (16) for fastening the drive means to the journal and a second nut (14) for fastening the drive means to the turbine shaft.Type: ApplicationFiled: November 6, 2014Publication date: October 13, 2016Inventors: Roland Gilbert Michel Brault, Nathalie Nowakowski
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Publication number: 20160169014Abstract: The invention relates to a turbine engine impeller, comprising a disc bearing vanes, the roots of which are fitted in grooves which are substantially parallel to an axis of revolution of the disc, the root of each vane being connected to a blade by an integrated platform, the platforms of said vanes cooperating so as to form a radially inner wall of a duct for a flow passing through the blades, the impeller further comprising two independent annular plates which are fixed to the disc, a first of said plates being mounted upstream of the disc and comprising a transverse annular portion which is supported on an upstream face of the roots of the vanes, and a second of said plates being mounted downstream of the disc and comprising a transverse annular portion which is supported on a downstream face of the roots of the vanes, characterised in that the integrated platform of each vane stops axially, upstream and downstream, to the right of the upstream and downstream transverse faces of the root, in that said tranType: ApplicationFiled: December 10, 2015Publication date: June 16, 2016Inventors: Jean-Philippe Antoine Beaujard, Roland Gilbert Michel Brault, Nathalie Nowakowski
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Patent number: 9341079Abstract: A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring.Type: GrantFiled: May 31, 2011Date of Patent: May 17, 2016Assignee: SNECMAInventors: Serge Louis Antunes, Michel Brault
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Publication number: 20130156574Abstract: A structure for an aircraft turbojet including a rolling bearing including an outer ring, a bearing bracket, a retaining ring interposed between the ring and the bracket, a mechanism to connect the ring onto the bracket incorporating an attaching flange installed on the bearing bracket, a flexible connection attached to the ring and to the flange, and a mechanism enabling axial retention of the ring, in event the flexible connection fractures. The mechanism enabling axial retention includes a first stop securely attached to the retaining ring and capable of axially retaining this retaining ring relative to the bracket, and a second stop securely attached to the retaining ring, and capable of axially retaining the ring relative to the retaining ring.Type: ApplicationFiled: May 31, 2011Publication date: June 20, 2013Applicant: SNECMAInventors: Serge Louis Antunes, Michel Brault
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Patent number: 7458773Abstract: A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine rotor blades respectively driving first and second low-pressure shafts in rotation; and a fan section comprising a first row of fan blades mounted on a front fan shaft that is connected to an upstream end of the first low-pressure shaft, and a second row of fan blades axially offset from the first row and mounted on a rear fan shaft that is connected to an upstream end of the second low-pressure shaft, the front fan shaft being connected to the upstream end of the first low-pressure shaft via a removable sleeve for transmitting torque.Type: GrantFiled: August 12, 2005Date of Patent: December 2, 2008Assignee: SNECMAInventors: Michel Brault, Jean-Claude Taillant
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Publication number: 20070059164Abstract: The present invention relates to a turbine module for a gas turbine engine comprising at least one turbine disk (3) and a disk-shaped component (5) mounted on the turbine disk upstream relative to the gas flow, said module comprising a means of assembly to the compressor of said engine, wherein the component (5) is preassembled to the turbine disk (3), before the module is assembled to the compressor, by bolting to an attachment flange (31) fixedly attached to the turbine disk (3).Type: ApplicationFiled: April 28, 2006Publication date: March 15, 2007Applicant: SNECMAInventors: Michel Brault, Maurice Judet, Thomas Langevin, Patrick Pasquis
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Publication number: 20070006569Abstract: A turbomachine comprising: a gas generator for producing combustion gas; a turbine section through which the combustion gas passes and comprising first and second rows of contrarotating turbine rotor blades respectively driving first and second low-pressure shafts in rotation; and a fan section comprising a first row of fan blades mounted on a front fan shaft that is connected to an upstream end of the first low-pressure shaft, and a second row of fan blades axially offset from the first row and mounted on a rear fan shaft that is connected to an upstream end of the second low-pressure shaft, the front fan shaft being connected to the upstream end of the first low-pressure shaft via a removable sleeve for transmitting torque.Type: ApplicationFiled: August 12, 2005Publication date: January 11, 2007Applicant: SNECMAInventors: Michel Brault, Jean-Claude Taillant
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Publication number: 20060245925Abstract: The invention relates to a device for balancing a turbomachine rotor comprising at least one counterweight 20 fitted to the rotor, characterized in that the counterweight 20 comprises two radial bearing surfaces 23, 24 oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces 10A1, 10B1 made on the rotor, the counterweight 20 being held against the rotor by an axial retention means. In particular, the axial retention means is a bolt 30 with a nut 32, the bolt holding the counterweight against a coupling flange 10 fixedly attached to the rotor, comprising an axial bearing surface 10B and the said radial bearing surfaces 10A1, 10B1.Type: ApplicationFiled: April 18, 2006Publication date: November 2, 2006Applicant: SNECMAInventors: Michel Brault, Maurice Judet, Thomas Langevin
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Publication number: 20060110244Abstract: The invention relates to a turbomachine comprising a rotor with a drive shaft centered on the axis of the turbomachine by a first bearing and a second bearing which bearings are supported respectively by a first-bearing-support piece and a second-bearing-support piece which are secured to one another and connected to the turbomachine fixed structure by a decoupling device. This turbomachine comprises means designed to collaborate with at least one element of the turbomachine fixed structure in order to perform a dual function, that of preventing the bearing supports, from rotating and that of radially retaining the drive shaft in the event of the bearings becoming decoupled.Type: ApplicationFiled: November 18, 2005Publication date: May 25, 2006Applicant: SNECMAInventors: Michel Brault, Patrick Morel, Zoltan Zsiga, Gael Bouchy, Pierre Pandelakis
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Patent number: 6655920Abstract: A spacer (36) made to be installed between two permanently connected discs (31 and 32), without a bolted flange, and comprising axial thrust (43, 47) as well as outer radial thrust (45, 48) alignment surfaces (41). It comprises moreover an outer cover (37) to provide sealing and a cooling passageway, and stiffening tongues (38) which accommodate thrust loads.Type: GrantFiled: June 3, 2002Date of Patent: December 2, 2003Assignee: SNECMA MoteursInventors: Bruno Beutin, Michel Brault, Pascal Gervais, Elisabeth Guigli, Monique Thore
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Publication number: 20020187046Abstract: A spacer (36) made to be installed between two permanently connected discs (31 and 32), without a bolted flange, and comprising axial thrust (43, 47) as well as outer radial thrust (45, 48) alignment surfaces (41). It comprises moreover an outer cover (37) to provide sealing and a cooling passageway, and stiffening tongues (38) which accommodate thrust loads.Type: ApplicationFiled: June 3, 2002Publication date: December 12, 2002Applicant: SNECMA MOTEURSInventors: Bruno Beutin, Michel Brault, Pascal Gervais, Elisabeth Guigli, Monique Thore