Patents by Inventor Anne-Marie Arraitz
Anne-Marie Arraitz 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: 20180179898Abstract: A nozzle sector for a turbine engine. The nozzle sector includes a radially outer platform, a radially inner platform, a first end blade, a second end blade and at least one first central blade between the end blades in a circumferential direction of the platforms. The blades extend radially between the platforms in the direction of the span of said blades. The sector includes means for cooling the blades, configured to cool each of the blades by circulating cooling air over same. The cooling means are configured to cool the one or more central blades more than at least one of the end blades.Type: ApplicationFiled: September 15, 2016Publication date: June 28, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Olivier Jean Daniel BAUMAS, Anne-Marie ARRAITZ, Anthony Pierre BEGUIN, Pragash DOUGLAS
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Patent number: 7360987Abstract: A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent inter-sector zones of stator elements being in radial alignment, said zones being defined between two adjacent sectors of the same stator element, and so as to repeat said distribution pattern around the entire circumference of the stator.Type: GrantFiled: March 7, 2005Date of Patent: April 22, 2008Assignee: SnecmaInventors: Anne-Marie Arraitz, Thierry Fachat, Jerome Friedel, Alain Gendraud, Delphine Roussin
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Patent number: 7309209Abstract: A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.Type: GrantFiled: March 7, 2005Date of Patent: December 18, 2007Assignee: Snecma MoteursInventors: Denis Amiot, Anne-Marie Arraitz, Thierry Fachat, Alain Gendraud, Delphine Roussin
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Publication number: 20070264120Abstract: A device for tuning clearance at rotor blade tips in a gas turbine rotor, the device comprising at least one annular air flow duct that is mounted around the circumference of an annular casing of a stator of the turbine, the annular air flow duct being designed to discharge air onto the casing in order to modify the temperature thereof. A tubular air manifold is disposed around the air flow duct(s). There are also disposed an air feed tube to supply the tubular air manifold with air and an air pipe opening in the tubular air manifold and opening out into the air flow duct(s). The air pipe is provided with a balancing diaphragm for balancing the air flowing through the pipe.Type: ApplicationFiled: March 7, 2005Publication date: November 15, 2007Applicant: SNECMA MOTEURSInventors: Denis Amiot, Anne-Marie Arraitz, Thierry Fachat, Alain Gendraud, Delphine Roussin
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Patent number: 7287955Abstract: A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes air circulation means for circulating air, said means being made up of at least three ducts; air supply means for supplying air to the air flow ducts; and air discharge means for discharging air on the ridges in order to modify the temperature, the air discharge means for each duct being made up of at least one top row having a number N of perforations disposed facing one of the side faces of the ridges and of at least one bottom row having a number 2N of perforations disposed facing a connection radius that connects the ridges to the casing.Type: GrantFiled: January 10, 2005Date of Patent: October 30, 2007Assignee: Snecma MoteursInventors: Denis Amiot, Anne-Marie Arraitz, Thierry Fachat, Alain Gendraud, Pascal Lefebvre, Delphine Roussin-Moynier
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Publication number: 20050238477Abstract: A method of assembling sectored elements of an annular stator of a high-pressure turbine of a turbomachine about a longitudinal axis of said turbine, in which method an angular distribution pattern is defined for distributing elements of the stator over a predetermined angular sector, said pattern being defined so as to prevent inter-sector zones of stator elements being in radial alignment, said zones being defined between two adjacent sectors of the same stator element, and so as to repeat said distribution pattern around the entire circumference of the stator.Type: ApplicationFiled: March 7, 2005Publication date: October 27, 2005Applicant: SNECMA MOTEURSInventors: Anne-Marie Arraitz, Thierry Fachat, Jerome Friedel, Alain Gendraud, Delphine Roussin
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Publication number: 20050158169Abstract: A clearance control device for controlling clearance between rotary blade tips and a stationary bushing of a gas turbine having a casing that is provided with at least two annular ridges, the clearance control device including a circular tuning unit that includes air circulation means for circulating air, said means being made up of at least three ducts; air supply means for supplying air to the air flow ducts; and air discharge means for discharging air on the ridges in order to modify the temperature, the air discharge means for each duct being made up of at least one top row having a number N of perforations disposed facing one of the side faces of the ridges and of at least one bottom row having a number 2N of perforations disposed facing a connection radius that connects the ridges to the casing.Type: ApplicationFiled: January 10, 2005Publication date: July 21, 2005Applicant: SNECMA MOTEURSInventors: Denis Amiot, Anne-Marie Arraitz, Thierry Fachat, Alain Gendraud, Pascal Lefebvre, Delphine Roussin-Moynier
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Patent number: 6666645Abstract: An arrangement for adjusting the diameter of a gas turbine stator includes a casing having a main portion and rings bordering a vein of a gas flow and located in front of respective levels of mobile blades of a rotor, and communication passages of a gas flow under pressure. The rings are surrounded by the casing and fixed thereto by circular groups of spacers. The rings include a wall extending from the casing to one of the rings and separating two chambers. The wall includes an outside edge curved into a spacer hook and engaged between the main portion of the casing and a respective appendage curved into a casing hook associated with the spacer hook. The communication passages of the gas flow under pressure exist between the chambers. At least one of the communication passages is realized by cavities through a junction of hooks.Type: GrantFiled: September 6, 2001Date of Patent: December 23, 2003Assignee: Snecma MoteursInventors: Jean-Baptiste Arilla, Anne-Marie Arraitz, Alain Dominique Gendraud
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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