Patents by Inventor Delphine Roussin
Delphine Roussin 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: 9004852Abstract: A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.Type: GrantFiled: October 16, 2009Date of Patent: April 14, 2015Assignee: SNECMAInventors: Mathieu Dakowski, Fabrice Garin, Delphine Roussin-Leroux, Wilfried Schweblen
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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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Patent number: 8662828Abstract: A high pressure turbine of a turbomachine such as a turbojet, in which a control box of radial clearances of rotating blades are provided. An annular element including a determined flexibility has one end fixed to an annular support and the other end supported by a simple axial bearing with a given pressure on the upstream side of the control box. Thus, disturbing vibration loads are prevented at the attachment points of the control box with the external casing of turbines, thereby also eliminating the risk of cracks occurring.Type: GrantFiled: May 25, 2009Date of Patent: March 4, 2014Assignee: SNECMAInventors: Alain Dominique Gendraud, Delphine Roussin-Leroux, Jean-Luc Le Strat, Pascal Tatiossian
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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: 20110280735Abstract: A turbomachine high-pressure turbine including a rotor disc with upstream and downstream annular flanges separating a radially internal annular cavity in which the hub of the disc extends from two radially external annular cavities, of which one is upstream of the disc and receives a ventilation air flow and of which the other is downstream of the disc, the upstream flange of the disc including a mechanism connecting to the upstream eternal cavity and the internal cavity for ventilating the hub of the disc.Type: ApplicationFiled: October 16, 2009Publication date: November 17, 2011Applicant: SNECMAInventors: Mathieu Dakowski, Fabrice Garin, Delphine Roussin-Leroux, Wilfried Schweblen
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Patent number: 7584618Abstract: A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to predetermined clearance between the rotor and the turbine shroud. The system further comprises means for calculating at least one second control signal based on a second setpoint value different from the first value representative of clearance in the turbine, and selector means for-selecting the second control signal to control the regulator valve in response to one or more engine parameters. With such a system, it is possible to control the air flow applied to the shroud in application of a plurality of control logic systems.Type: GrantFiled: June 14, 2005Date of Patent: September 8, 2009Assignee: SnecmaInventors: Denis Amiot, Frederick Duny, Jérôme Friedel, Christian Kaincz, Delphine Roussin-Moynier
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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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Patent number: 7296415Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.Type: GrantFiled: October 21, 2004Date of Patent: November 20, 2007Assignee: Snecma MoteursInventors: Sylvie Coulon, Delphine Roussin, Martine Bes
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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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Patent number: 7201559Abstract: A stationary ring assembly forming a rotor shroud for a gas turbine including a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween. The sealing means include at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments. At least one end of each radial slot opens out into the corresponding axial slot, each axial slot of a segment presents a depth that is greater than the depth of the corresponding radial slot, and the axial sealing strip presents a width that is greater than the width of the radial strip.Type: GrantFiled: April 21, 2005Date of Patent: April 10, 2007Assignee: SnecmaInventors: Alain Gendraud, Delphine Roussin-Moynier
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Patent number: 7114914Abstract: A device for controlling the clearance between the tips of rotary blades and a stationary ring assembly of a gas turbine, the device comprising a circular control box having at least two annular air circulation strips that are spaced apart from each other in the axial direction, each having a plurality of perforations in order to modify the temperature of the stationary ring assembly by discharging air, an annular air feed channel radially spaced from the air circulation strip, at least one air duct for feeding the feed channel with air, and a plurality of hollow distribution spacers connecting the air feed channel to the air circulation strips in order to feed the strips with air while enabling the air that has been discharged against the stationary ring assembly to flow between the feed channel and the circulation strips in order to be evacuated therefrom.Type: GrantFiled: July 22, 2004Date of Patent: October 3, 2006Assignee: Snecma MoteursInventors: Alain Gendraud, Delphine Roussin, David Audeon
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Publication number: 20050276690Abstract: A system for controlling a flow of air applied to a gas turbine shroud in an airplane engine, the air flow being adjusted by a regulator valve of position that is controlled by a first control signal calculated on the basis of a first setpoint value corresponding to predetermined clearance between the rotor and the turbine shroud. The system further comprises means for calculating at least one second control signal based on a second setpoint value different from the first value representative of clearance in the turbine, and selector means for-selecting the second control signal to control the regulator valve in response to one or more engine parameters. With such a system, it is possible to control the air flow applied to the shroud in application of a plurality of control logic systems.Type: ApplicationFiled: June 14, 2005Publication date: December 15, 2005Applicant: SNECMA MOTEURSInventors: Denis Amiot, Frederick Duny, Jerome Friedel, Christian Kaincz, Delphine Roussin-Moynier
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Publication number: 20050248100Abstract: A stationary ring assembly forming a rotor shroud for a gas turbine, the stationary ring assembly comprising a plurality of segments having adjacent side faces that are placed end to end with sealing means interposed therebetween, the sealing means comprising at least one axial sealing strip and at least one radial sealing strip respectively received in axial slots and in radial slots formed facing one another in the adjacent side faces of the segments, at least one end of each radial slot opening out into the corresponding axial slot, each axial slot of a segment presenting a depth that is greater than the depth of the corresponding radial slot, and the axial sealing strip presenting a width that is greater than the width of the radial strip.Type: ApplicationFiled: April 21, 2005Publication date: November 10, 2005Applicant: Snecma MoteursInventors: Alain Gendraud, 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: 20050169749Abstract: This invention refers to a labyrinth seal for a gas turbine engine incorporating from upstream to downstream ends, a high pressure compressor with a rotor, a diffuser and a fixed wall element forming at least one part of the internal envelope of the combustion chamber said seal comprising a stator part mounted on the wall element by virtue of an attaching part with flanges and supporting an annular wearing part said wearing part working jointly with a rotor element provided with at least one circumferential tooth integral with rotor of the compressor to form the labyrinth seal. It is characterized by the fact that at least one of the flanges of said attaching means is heavy enough to harmonize the rate of dilatation of the stator part with respect to the dilatation rate of the rotor element during engine accelerations. In conformity with another characteristic, ventilation orifices are arranged in the wall element.Type: ApplicationFiled: October 21, 2004Publication date: August 4, 2005Applicant: SNECMA MOTEURSInventors: Sylvie Coulon, Delphine Roussin, Martine Bes
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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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Publication number: 20050042080Abstract: A device for controlling the clearance between the tips of rotary blades and a stationary ring assembly of a gas turbine, the device comprising a circular control box having at least two annular air circulation strips that are spaced apart from each other in the axial direction, each having a plurality of perforations in order to modify the temperature of the stationary ring assembly by discharging air, an annular air feed channel radially spaced from the air circulation strip, at least one air duct for feeding the feed channel with air, and a plurality of hollow distribution spacers connecting the air feed channel to the air circulation strips in order to feed the strips with air while enabling the air that has been discharged against the stationary ring assembly to flow between the feed channel and the circulation strips in order to be evacuated therefrom.Type: ApplicationFiled: July 22, 2004Publication date: February 24, 2005Applicant: SNECMA MOTEURSInventors: Alain Gendraud, Delphine Roussin, David Audeon