Patents by Inventor Eric Stephan Bil
Eric Stephan Bil 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: 8959926Abstract: A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.Type: GrantFiled: May 19, 2009Date of Patent: February 24, 2015Assignee: SNECMAInventors: Eric Stephan Bil, Michel Gilbert Roland Brault
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Patent number: 8800291Abstract: A diffuser which straightens the flow of air issuing from a centrifugal compressor in a turbine engine is provided. The diffuser having a cylindrical shape and including a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part, and a third part intended to open out into a downstream cavity, positioned downstream of the diffuser and fed with air issuing from the compressor. The first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the downstream cavity into communication with a bleed cavity situated upstream of the diffuser.Type: GrantFiled: June 21, 2011Date of Patent: August 12, 2014Assignee: SNECMAInventors: Eric Stephan Bil, Jean-Francois Rios, Delphine Roussin-Leroux
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Publication number: 20110314828Abstract: Diffuser intended to straighten the flow of air issuing from a centrifugal compressor in a turbine engine, the said diffuser having a cylindrical shape and comprising a first part having the form of two substantially parallel discs extending substantially radially relative to the axis of symmetry of the diffuser, a second bent part and a third part intended to open out into a downstream cavity, positioned downstream of the said diffuser and fed with air issuing from the said compressor, characterized in that the first part is traversed by a plurality of channels distributed evenly over its circumference and opening out on its downstream face so as to bring the air contained in the said downstream cavity into communication with a bleed cavity situated upstream of the said diffuser.Type: ApplicationFiled: June 21, 2011Publication date: December 29, 2011Applicant: SNECMAInventors: Eric Stéphan BIL, Jean-Francois Rios, Delphine Roussin-Leroux
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Publication number: 20110072829Abstract: A turbomachine including an intermediate casing including, fastened to the end thereof, an outer casing of a high pressure compressor, and an air bleed mechanism bleeding air downstream from the stream through the compressor and including an outlet connected to an air reinjection mechanism reinjecting air upstream from the compressor via an annular manifold surrounding the inner wall of the intermediate casing and situated radially between the inner wall and an outer wall defining a secondary flow stream of the turbomachine.Type: ApplicationFiled: May 19, 2009Publication date: March 31, 2011Applicant: SNECMAInventors: Eric Stephan Bil, Michel Gilbert Roland Brault
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Patent number: 7785066Abstract: The bypass turbomachine comprises, between a primary flowpath (2) and a secondary flowpath (3), a structural intermediate casing (14). A bleed passage (29) allows the diversion of a portion of the gas stream toward the secondary flowpath (3), downstream of support arms (18) situated at the periphery of the intermediate casing. A bleed opening (28) emerges upstream of the support arms (18). A slide valve (22) slides between three positions, namely a closed position in which the slide valve (22) completely blocks off the bleed passage and opening, an intermediate position in which the bleed opening (28) emerging upstream of the support arms (18) is blocked off, while the bleed passage (29) for diverting a portion of the gas stream downstream of the support arms (18) is open, and an open position in which the bleed opening (28) emerging upstream of the support arms (18) and the bleed passage (29) emerging downstream of the support arms are both open.Type: GrantFiled: May 31, 2007Date of Patent: August 31, 2010Assignee: SNECMAInventors: Eric Stephan Bil, Gilles Alain Charier, Philippe Jacques Pierre Fessou, Patrick Charles Georges Morel
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Patent number: 7618232Abstract: This turbine engine compressor comprises a separating nose extended by inner and outer annular walls defining in cooperation an annular volume (V) of separation of a primary flow (F1) and a secondary flow (F2). This volume (V) comprises a plurality of annular segments in the form of cells separated in pairs by blades of a first fan, these blades passing through both the primary flow (F1) and the secondary flow (F2). These cells are fixed to an upstream annular collar and a downstream annular collar driven rotationally by the aforementioned blades.Type: GrantFiled: August 21, 2006Date of Patent: November 17, 2009Assignee: SnecmaInventors: Eric Stephan Bil, Gilles Alain Marie Charier
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Patent number: 7399163Abstract: Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.Type: GrantFiled: August 18, 2005Date of Patent: July 15, 2008Assignee: SNECMAInventors: Eric Stephan Bil, Chantal Gisele Giot, Thomas Schlesinger
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Patent number: 6457935Abstract: A sheet metal sealing sleeve placed under a pair of juxtaposed blade platforms in a turbomachine so as to cover the gap between them is provided with apertures to allow the flow of a ventilating gas to the platforms. The apertures are provided in bosses formed on the sleeve to define chambers between the sleeve and the platforms which provide for greater heat exchange by virtue of the forcible impact of the gas blown through the apertures under the platforms. The sleeve also aids in damping platform vibration.Type: GrantFiled: June 20, 2001Date of Patent: October 1, 2002Assignee: SNECMA MoteursInventors: Serge Louis Antunes, Eric Stephan Bil, Isabelle Monique Marie Bourriaud, Maurice Guy Judet
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Patent number: 6328531Abstract: A cooled turbine blade comprising a platform and an aerofoil portion has a rebate formed in the aerofoil portion near the trailing edge on the pressure face side. This rebate extends from the platform to the blade tip, and slots for the escape of cooling air from an internal cavity of the aerofoil portion open into the rebate.Type: GrantFiled: October 5, 1999Date of Patent: December 11, 2001Assignee: Societe Nationale d'Etude et de Construction de Moteurs d'Aviation “Snecma”Inventors: Christian Bernard Bariaud, Eric Stéphan Bil
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Patent number: 6163959Abstract: A method of reducing the gap between a liner and a turbine distributor of a turbojet engine. The method allows for the improvement of the seal on the inside of the distributor of the high pressure turbine at the lower platform. The method includes the steps of: applying a protective deposit to the lower part of the external surface of the liner, before carrying out a filling by diffusion brazing between the liner and the distributor. The protective deposit, preferably a anti-adherent ceramic, makes it possible for the braze to avoid fixing the liner onto the distributor at the lower platform level. The method also has applications to turbojet engines.Type: GrantFiled: March 19, 1999Date of Patent: December 26, 2000Assignee: Societe Nationale d'etude et de Construction de Moteurs d'Aviation "S.N.E.C.M.A."Inventors: Anne-Marie Arraitz, Eric Stephan Bil, Michel Gerard Paul Hacault, Laurent Philippe Yves Leray, Michel Jean Loubet, Marc Roger Marchi, Jean Manuel Morcillo, Didier Marie Mortgat, Michel Jean-Pierre Pernot, Thierry Christian Sanz
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Patent number: 5997247Abstract: This seal (6) running between gaps (6) between two stator sectors of a gas urbine engine is made up of several thin flexible slabs, capable of sliding one over the other, which gives a better seal.Type: GrantFiled: January 14, 1998Date of Patent: December 7, 1999Assignee: Societe Nationale Detude et de Construction de Mothers d'aviation "Snecma"Inventors: Anne-Marie Arraitz, Eric Stephan Bil, Michel Gerard Paul Hacault, Laurent Philippe Yves Leray, Marc Roger Marchi, Didier Marie Mortgat