Patents by Inventor Pierre-Alain Masserey
Pierre-Alain Masserey 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: 10260349Abstract: The disclosure provides a turbine blade. A turbine blade includes a shroud at a tip of the blade and an airfoil having a leading edge extending between the shroud and a root of the blade; a cutout portion extending at least along the leading edge of the airfoil nearest the shroud; an insert welded to the cutout portion at a weld region; and a weld-free region located between the insert and the cutout portion nearest the shroud.Type: GrantFiled: December 13, 2016Date of Patent: April 16, 2019Assignee: General Electric CompanyInventors: Francesco Piraccini, Andreas Helmut Kaiser, Pierre-Alain Masserey, Arnd Neuer
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Patent number: 10006296Abstract: A method and a blade for a turbine or, more generally a turbomachine, are described with the blade having at a top end a shroud segment designed to engage with shroud segments of adjacent blades in an ring-shaped assembly at least partly by means of assembling the blades with the shroud segment having a central indentation along an engaging face.Type: GrantFiled: May 23, 2013Date of Patent: June 26, 2018Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Dilli Prasad Ramannagari, Pierre-Alain Masserey, Ross Brian Fleming, Christina Calcagni
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Publication number: 20180100397Abstract: The disclosure provides a turbine blade. A turbine blade includes a shroud at a tip of the blade and an airfoil having a leading edge extending between the shroud and a root of the blade; a cutout portion extending at least along the leading edge of the airfoil nearest the shroud; an insert welded to the cutout portion at a weld region; and a weld-free region located between the insert and the cutout portion nearest the shroud.Type: ApplicationFiled: December 13, 2016Publication date: April 12, 2018Inventors: Francesco Piraccini, Andreas Helmut Kaiser, Pierre-Alain Masserey, Arnd Neuer
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Patent number: 8636475Abstract: A turbomachine includes a turbine stage having a plurality of blades including a first and a second blade disposed adjacent to each other, each blade having a radial longitudinal axis and a blade tip and configured to twist around the radial longitudinal axis in an operating state in a twist direction, wherein the first and the second blades are pretwisted in a direction of twist in a non-operating state, and wherein a connecting element interconnects the first and the second blades to each other in a circumferential direction in a region of the respective blade tip so as to maintain the pretwisting.Type: GrantFiled: November 30, 2009Date of Patent: January 28, 2014Assignee: Alstom Technology LtdInventors: Pierre-Alain Masserey, Rolf Hunziker, Benedikt Wanner, Christoph Gerber
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Publication number: 20130323053Abstract: A method and a blade for a turbine or, more generally a turbomachine, are described with the blade having at a top end a shroud segment designed to engage with shroud segments of adjacent blades in an ring-shaped assembly at least partly by means of assembling the blades with the shroud segment having a central indentation along an engaging face.Type: ApplicationFiled: May 23, 2013Publication date: December 5, 2013Applicant: ALSTOM Technology LtdInventors: Dilli Prasad Ramannagari, Pierre-Alain Masserey, Ross Brian Fleming, Christina Calcagni
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Patent number: 8425193Abstract: A rotating blade row is provided for the final stage of a steam turbine has blades with an integrated shroud. The shroud of each blade has a projection in the axial direction, in each case on its pressure side, which prevents droplets in the working fluid of the steam turbine from reaching the shroud fillet of the respective subsequent blade in the flow direction. The shroud fillet is therefore protected against erosion damage caused by droplets impact erosion. The projection is positioned and of such a size that mass equilibrium is ensured between the suction side and the pressure side of the shroud, and stress equilibrium is ensured between the projection on the pressure side and the suction-side shroud. The projection furthermore has a recess between its greatest axial extent and the leading edge.Type: GrantFiled: March 24, 2011Date of Patent: April 23, 2013Assignee: ALSTOM Technology LtdInventors: Pierre-Alain Masserey, Rolf Hunziker, Benedikt Wanner
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Patent number: 8376710Abstract: The disclosure relates to adjacently mounted circumferentially distributed turbo machine airfoils with a vibration damping system. Each adjacent pair of airfoils includes a fixing and receiving portion, extending between the paired adjacent airfoils, each with a face that are proximal (e.g., in contact with) each other. Vibration can be suppressed by the fixing and receiving portions each having a received magnet fixingly installed therein and a non-magnetic conducting plate therebetween. Each magnet has a pole that faces the pole of the other magnet in between which the non-magnetic conducting plate is located and in which eddy currents can be induced by the relative movement of the magnets due to vibration.Type: GrantFiled: May 7, 2010Date of Patent: February 19, 2013Assignee: Alstom Technology Ltd.Inventors: Christoph Gerber, Markus Denk, Pierre-Alain Masserey, Jacob Laborenz, Christian Siewert
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Patent number: 8333555Abstract: An exemplary control stage of a steam turbine is disclosed, which includes plural staging valves circumferentially distributed around the turbine for regulating steam admission flow so as to control the loading of the turbine. Nozzle chambers are connected to a downstream end of each staging valve. An arc of admission forms the downstream portion of each nozzle chamber, and control stage nozzles in the arcs of admission define the downstream end of the nozzle chamber. Each nozzle chamber has at least two arcs of admission, each with a different circumferential dimension.Type: GrantFiled: August 21, 2009Date of Patent: December 18, 2012Assignee: Alstom Technology Ltd.Inventors: Thomas Mokulys, Vishal Borikar, Giorgio Zanazzi, Pierre-Alain Masserey, Michael Sell
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Publication number: 20110268574Abstract: A rotating blade row is provided for the final stage of a steam turbine has blades with an integrated shroud. The shroud of each blade has a projection in the axial direction, in each case on its pressure side, which prevents droplets in the working fluid of the steam turbine from reaching the shroud fillet of the respective subsequent blade in the flow direction. The shroud fillet is therefore protected against erosion damage caused by droplets impact erosion. The projection is positioned and of such a size that mass equilibrium is ensured between the suction side and the pressure side of the shroud, and stress equilibrium is ensured between the projection on the pressure side and the suction-side shroud. The projection furthermore has a recess between its greatest axial extent and the leading edge.Type: ApplicationFiled: March 24, 2011Publication date: November 3, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Pierre-Alain MASSEREY, Rolf HUNZIKER, Benedikt WANNER
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Publication number: 20100290893Abstract: The disclosure relates to adjacently mounted circumferentially distributed turbo machine airfoils with a vibration damping system. Each adjacent pair of airfoils includes a fixing and receiving portion, extending between the paired adjacent airfoils, each with a face that are proximal (e.g., in contact with) each other. Vibration can be suppressed by the fixing and receiving portions each having a received magnet fixingly installed therein and a non-magnetic conducting plate therebetween. Each magnet has a pole that faces the pole of the other magnet in between which the non-magnetic conducting plate is located and in which eddy currents can be induced by the relative movement of the magnets due to vibration.Type: ApplicationFiled: May 7, 2010Publication date: November 18, 2010Applicant: ALSTOM TECHNOLOGY LTDInventors: Christoph Gerber, Markus Denk, Pierre-Alain Masserey, Jacob Laborenz, Christian Siewert
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Publication number: 20100135775Abstract: A turbomachine includes a turbine stage having a plurality of blades including a first and a second blade disposed adjacent to each other, each blade having a radial longitudinal axis and a blade tip and configured to twist around the radial longitudinal axis in an operating state in a twist direction, wherein the first and the second blades are pretwisted in a direction of twist in a non-operating state, and wherein a connecting element interconnects the first and the second blades to each other in a circumferential direction in a region of the respective blade tip so as to maintain the pretwisting.Type: ApplicationFiled: November 30, 2009Publication date: June 3, 2010Applicant: ALSTOM TECHNOLOGY LTDInventors: Pierre-Alain Masserey, Rolf Hunziker, Benedikt Wanner, Christoph Gerber
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Publication number: 20100047064Abstract: An exemplary control stage of a steam turbine is disclosed, which includes plural staging valves circumferentially distributed around the turbine for regulating steam admission flow so as to control the loading of the turbine. Nozzle chambers are connected to a downstream end of each staging valve. An arc of admission forms the downstream portion of each nozzle chamber, and control stage nozzles in the arcs of admission define the downstream end of the nozzle chamber. Each nozzle chamber has at least two arcs of admission, each with a different circumferential dimension.Type: ApplicationFiled: August 21, 2009Publication date: February 25, 2010Applicant: ALSTOM Technology Ltd.Inventors: Thomas MOKULYS, Vishal BORIKAR, Giorgio ZANAZZI, Pierre-Alain MASSEREY, Michael SELL
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Patent number: 7300256Abstract: A damping arrangement for a blade (20) of an axial turbine, in particular a gas turbine, includes a damping element (17) which is arranged in a recess (16) in the blade aerofoil (10) of the blade (20) and frictionally dampens the vibrations of the blade (20). In such a damping arrangement, simplified manufacture and assembly and a reliable and effective function are achieved by the recess being configured as a cavity (16) extending in the radial direction through the inside of the blade aerofoil (10), the damping element (17) being inserted in the radial direction into said cavity (16).Type: GrantFiled: November 29, 2004Date of Patent: November 27, 2007Assignee: ALSTOM Technology Ltd.Inventors: Pierre-Alain Masserey, Dariusz Szwedowicz, Jaroslaw Szwedowicz
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Publication number: 20070253828Abstract: A damping arrangement for a blade (20) of an axial turbine, in particular a gas turbine, includes a damping element (17) which is arranged in a recess (16) in the blade aerofoil (10) of the blade (20) and frictionally dampens the vibrations of the blade (20). In such a damping arrangement, simplified manufacture and assembly and a reliable and effective function are achieved by the recess being configured as a cavity (16) extending in the radial direction through the inside of the blade aerofoil (10), the damping element (17) being inserted in the radial direction into said cavity (16).Type: ApplicationFiled: November 29, 2004Publication date: November 1, 2007Inventors: Pierre-Alain Masserey, Dariusz Szwedowicz, Jaroslaw Szwedowicz