Patents by Inventor Christophe Bernard Texier
Christophe Bernard Texier 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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Publication number: 20230047952Abstract: An assembly for a turbomachine extending along an axis includes a combustion chamber having, at its downstream end, a downstream flange having a radially extending part. The assembly further includes a distributor disposed downstream of the combustion chamber and having a platform from which at least one vane extends radially. The platform includes an upstream flange extending radially and delimiting, with the radial part of the downstream flange disposed opposite it. An annular space for the circulation of cooling air opens into the combustion chamber at its radially internal end and has, at its radially external end, means of sealing attached to the distributor.Type: ApplicationFiled: January 20, 2021Publication date: February 16, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Paul Olivier DANRE, Jean-Luc BACHA, Julie Laure Antoinette BUREL, Julien Michel TAMIZIER, Christophe Bernard TEXIER
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Patent number: 11221141Abstract: A turbomachine includes a combustion chamber with a radially extending downstream flange at its downstream end. A distributor is disposed downstream of the combustion chamber and includes a platform from which at least one vane extends radially. The platform has an upstream edge extending radially and delimiting, with the downstream flange disposed opposite, a gap opening into the combustion chamber at its radially inner end and closed at its radially outer end by sealing means fixed to the distributor. The downstream flange of the combustion chamber has at least one rectilinear cooling orifice passing through the flange and opening into the gap opposite the platform of the distributor.Type: GrantFiled: July 18, 2019Date of Patent: January 11, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julien Michel Tamizier, Christophe Bernard Texier, Damien Bonneau, Damien Bonnefoi, François Xavier Chapelle
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Publication number: 20210302018Abstract: A turbomachine includes a combustion chamber with a radially extending downstream flange at its downstream end. A distributor is disposed downstream of the combustion chamber and includes a platform from which at least one vane extends radially. The platform has an upstream edge extending radially and delimiting, with the downstream flange disposed opposite, a gap opening into the combustion chamber at its radially inner end and closed at its radially outer end by sealing means fixed to the distributor. The downstream flange of the combustion chamber has at least one rectilinear cooling orifice passing through the flange and opening into the gap opposite the platform of the distributor.Type: ApplicationFiled: July 18, 2019Publication date: September 30, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Julien Michel Tamizier, Christophe Bernard Texier, Damien Bonneau, Damien Bonnefoi, François Xavier Chapelle
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Patent number: 8038410Abstract: When cold and in the uncoated state, the aerodynamic airfoil is substantially identical to a nominal airfoil determined by the Cartesian coordinates X, Y, Z? given in Table 1, in which the coordinate Z? is the ratio D/H where D is the distance from the point in question to a reference plane P0, located at the base of the nominal airfoil, and H is the height of this airfoil, measured from said reference plane up to the tip of the blade. The D and H measurements being taken radially with respect to the axis of the turbine whereas the X coordinate is measured in the axial direction of the turbine.Type: GrantFiled: February 21, 2008Date of Patent: October 18, 2011Assignee: SNECMAInventors: Gregory Pierre Lafarge, Philippe Picot, Christophe Bernard Texier
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Publication number: 20080206061Abstract: Optimized aerodynamic airfoil for a turbine blade When cold and in the uncoated state, the aerodynamic airfoil is substantially identical to a nominal airfoil determined by the Cartesian coordinates X, Y, Z? given in Table 1, in which the coordinate Z? is the ratio D/H where D is the distance from the point in question to a reference plane P0, located at the base of the nominal airfoil, and H is the height of this airfoil, measured from said reference plane up to the tip of the blade. The D and H measurements being taken radially with respect to the axis of the turbine whereas the X coordinate is measured in the axial direction of the turbine.Type: ApplicationFiled: February 21, 2008Publication date: August 28, 2008Applicant: SNECMAInventors: Gregory Pierre LAFARGE, Philippe PICOT, Christophe Bernard TEXIER
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Patent number: 6334755Abstract: The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.Type: GrantFiled: February 18, 2000Date of Patent: January 1, 2002Assignee: Snecma MoteursInventors: Xavier Gérard André Coudray, Mischaël François Louis Derrien, Marc Roger Marchi, Philippe Christian Pellier, Jean-Claude Christian Taillant, Thierry Henri Marcel Tassin, Christophe Bernard Texier, Isabelle Marie Monique Valente
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Patent number: 5993156Abstract: A turbine vane-system cooling system uses three internal cooling cavities 1, 12, 13) separated by two radial walls (9, 10). The upstream cavity (11) uses a helical ramp (30) and is fed through an intake (22) at the vane root (3). The middle cavity (12) also is fed at the vane root (3) and includes a compartmented, multi-perforated lining (40). The air is exhausted from each compartment through impact orifices and enters the succeeding compartment through slots (42) and then is finally exhausted through a vane-head orifice (21). The vane side walls opposite the downstream cavity (13) have double skins with bridging elements. The air passes through these double skins but circulates centrifugally in the upstream portion (15) of the downstream cavity (13) and enters this cavity's downstream portion (16) to be exhausted through slots (19) in the trailing edge (6). A third wall (14) divides the downstream cavity (13) into two parts (15, 16).Type: GrantFiled: June 25, 1998Date of Patent: November 30, 1999Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation SNECMAInventors: Yves Maurice Bailly, Xavier Gerard Andre Coudray, Mischael Francois Louis Derrien, jean-Michel Roger Fougeres, Philippe Christian Pellier, Jean-Claude Christian Taillant, Thierry Henri Marcel Tassin, Christophe Bernard Texier