Patents by Inventor Jean-Luc Bacha
Jean-Luc Bacha 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: 11795828Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.Type: GrantFiled: March 16, 2020Date of Patent: October 24, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Matthieu Simon, Jean-Luc Bacha, Paul Danre, Léandre Ostino
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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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Publication number: 20220170377Abstract: A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.Type: ApplicationFiled: March 16, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Matthieu SIMON, Jean-Luc BACHA, Paul DANRE, Léandre OSTINO
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Patent number: 9951636Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).Type: GrantFiled: December 20, 2013Date of Patent: April 24, 2018Assignee: SNECMAInventors: Jean Pierre Mareix, Emmanuel Berche, Jean Luc Bacha, Tangi Brusq
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Patent number: 9863263Abstract: A turbine wheel for a turbine engine is provided. The turbine wheel includes a disk carrying blades including internal channels for passing a flow of cooling air, each blade having a platform carrying an airfoil and connected by a tang to a root. The blade roots are engaged in grooves in the periphery of the disk and their tangs define between them spaces for housing sealing and damping members, which cooperate with the inside faces of the platforms to define air flow cavities. The tangs of at least some of the blades include cooling air outlet orifices that open out both into internal channels in the blades and into the cavities.Type: GrantFiled: October 24, 2012Date of Patent: January 9, 2018Assignee: SnecmaInventors: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq, Jean-Pierre Mareix
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Patent number: 9435210Abstract: A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall.Type: GrantFiled: December 4, 2012Date of Patent: September 6, 2016Assignee: SNECMAInventors: Jean-Luc Bacha, Emmanuel Berche, Tangi Brusq
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Publication number: 20150345317Abstract: The invention relates to a device for connection between two enclosures of a turbomachine, for enabling the circulation of a coolant between said enclosures, via said connection device, said connection device comprising an outer tube (2) having an opening (3) extending along the entire length of said outer tube (2), and also comprising an inner tube (6) extending inside the outer tube (2).Type: ApplicationFiled: December 20, 2013Publication date: December 3, 2015Inventors: Jean Pierre MAREIX, Emmanuel BERCHE, Jean Luc BACHA, Tangi BRUSQ
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Patent number: 8961137Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.Type: GrantFiled: April 17, 2012Date of Patent: February 24, 2015Assignee: SnecmaInventors: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq
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Patent number: 8684665Abstract: A turbine ring sector comprising a wall presenting an inside face and an outside face, in which the inside face defines an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage is disclosed. The multiply-perforated metal sheet has a bottom, and the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap. The variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value and then increases from the minimum value to a second maximum value.Type: GrantFiled: February 1, 2011Date of Patent: April 1, 2014Assignee: SNECMAInventors: Jean-Luc Bacha, Emmanuel Berche, Didier Jeannel
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Publication number: 20120269650Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.Type: ApplicationFiled: April 17, 2012Publication date: October 25, 2012Applicant: SNECMAInventors: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq
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Publication number: 20120141257Abstract: The segmented ring has the gaseous hot flow of the turbomachine passing through it and comprises: a plurality of segments assembled by means of sealed connection involving sealing strips, provided in the mutually-facing radial faces of said segments the internal lateral faces of which delimit the flow path along which the hot gaseous flow travels; and through-orifices, formed in said segments, to carry external fresh air towards their radial and internal faces. Advantageously, one, the lower one, of the sealing strips of the means of connection is designed to lie close to the lateral internal faces of said segments and to run parallel to them, passing through a cooling chamber formed in the radial faces of the segments and into which said orifices open.Type: ApplicationFiled: December 5, 2011Publication date: June 7, 2012Applicant: SNECMAInventors: Emmanuel Berche, Jean-Luc Bacha, Didier Fabre, Jean-Pierre Mareix
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Patent number: 8192145Abstract: A turbine nozzle sector that includes an outer platform segment and an inner platform segment between which there extends one or more hollow vanes is disclosed. Each vane presents a trailing edge cavity for feeding with cooling air and communicating with a plurality of vents distributed along the trailing edge of the vane, these vents serving to exhaust a fraction of the cooling air. The cavity communicates with an air outlet hole situated level with the outer platform and enabling a fraction of the cooling air to be exhausted.Type: GrantFiled: August 4, 2008Date of Patent: June 5, 2012Assignee: SNECMAInventors: Jean-Luc Bacha, Olivier Jean Daniel Baumas, Lucie Lanciaux, Sophie Lavison
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Publication number: 20110188993Abstract: A turbine ring sector comprising: a wall presenting an inside face and an outside face, the inside face defining an axially oriented airflow passage through which gas flows; and a multiply-perforated metal sheet situated on the side of the wall that is opposite from the airflow passage, said multiply-perforated metal sheet having a bottom; wherein the space between the outside face of the wall and the bottom of the multiply-perforated metal sheet defines a gap; and wherein the variation in the value of the gap over the entire axial extent thereof decreases from a first maximum value towards a minimum value, said minimum value defining the minimum of the gap, and then increases from the minimum value to a second maximum value.Type: ApplicationFiled: February 1, 2011Publication date: August 4, 2011Applicant: SNECMAInventors: Jean-Luc Bacha, Emmanuel Berche, Didier Jeannel
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Patent number: 7819628Abstract: An assembly includes a vane and a cooling liner for cooling the vane, the vane having a central cavity with at least one first opening into which the liner extends, the liner having a flange fixed to the rim of the opening. This assembly includes, near the flange, a peripheral insert inserted between the wall of the liner and the wall of the opening.Type: GrantFiled: March 28, 2007Date of Patent: October 26, 2010Assignee: SNECMAInventors: Alexandre Nicolas Dervaux, Olivier Jean Daniel Baumas, Jean-Luc Bacha
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Publication number: 20090041586Abstract: A turbine nozzle sector that comprises an outer platform segment and an inner platform segment between which there extend one or more hollow vanes. Each vane presents a trailing edge cavity for feeding with cooling air and communicating with a plurality of vents distributed along the trailing edge of the vane, these vents serving to exhaust a fraction of the cooling air. Said cavity communicates with an air outlet hole situated level with the outer platform and enabling a fraction of the cooling air to be exhausted.Type: ApplicationFiled: August 4, 2008Publication date: February 12, 2009Applicant: SNECMAInventors: Jean-Luc BACHA, Olivier Jean Daniel BAUMAS, Lucie LANCIAUX, Sophie LAVISON
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Publication number: 20070231150Abstract: The assembly of the invention is comprised of a vane (2) and of a cooling liner (6) for cooling the vane (2), the vane (2) comprising a central cavity (5) with at least one first opening (7) into which the liner (6) extends, the liner (6) comprising a flange (13) fixed to the rim (14) of the opening (7). This assembly is one which comprises, near the flange (13), a peripheral insert (16) inserted between the wall of the liner (6) and the wall (7?) of the opening (7). Thus the joint at the flange (13) is sealed.Type: ApplicationFiled: March 28, 2007Publication date: October 4, 2007Applicant: SNECMAInventors: Alexandre Nicolas DERVAUX, Olivier Jean Daniel Baumas, Jean-Luc Bacha