Patents by Inventor Hélène SAXER-FELICI
Hélène SAXER-FELICI 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: 9464529Abstract: A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.Type: GrantFiled: September 26, 2011Date of Patent: October 11, 2016Assignee: GENERAL ELECTRIC TECHNOLOGY GMBHInventors: Chiara Zambetti, Sergei Riazantsev, Hélène Saxer-Felici
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Publication number: 20120070309Abstract: A blade, for a gas turbine, includes a blade airfoil, having a shroud segment arranged on its upper end. The shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage. The side rails include rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.Type: ApplicationFiled: September 26, 2011Publication date: March 22, 2012Applicant: ALSTOM TECHNOLOGY LTD.Inventors: Chiara ZAMBETTI, Sergei RIAZANTSEV, Hélène SAXER-FELICI
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Patent number: 7520724Abstract: A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct.Type: GrantFiled: July 10, 2006Date of Patent: April 21, 2009Assignee: Alstom Technology LtdInventors: Shailandra Naik, Sacha Parneix, Ulrich Rathmann, Helene Saxer-Felici, Stefan Schlechtriem, Beat Von Arx
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Patent number: 7264445Abstract: A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.Type: GrantFiled: January 12, 2006Date of Patent: September 4, 2007Assignee: Alstom Technology LtdInventors: Shailandra Naik, Sacha Parneix, Ulrich Rathmann, Helene Saxer-Felici, Stefan Schlechtriem, Beat Von Arx
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Publication number: 20060292006Abstract: A cooled blade for a gas turbine has a blade airfoil, which emerges from a blade root and a blade shank and has a leading edge and a trailing edge and, within the blade airfoil, a plurality of sequential coolant ducts, in terms of flow, extending in a radial direction. A first coolant duct along the leading edge, and a second coolant duct along the trailing edge, have a main flow of a coolant flowing through them from the blade root to the tip of the blade airfoil. An inlet of the first coolant duct is in connection with a main coolant inlet, and an outlet of the first coolant duct is in connection with the inlet to the second coolant duct via a first deflection region. A third coolant duct is arranged between the first and the second coolant duct and a second deflection region. An additional flow of cooler coolant provided from outside is added from the third coolant duct into the heated main flow of the coolant flowing into the second coolant duct.Type: ApplicationFiled: July 10, 2006Publication date: December 28, 2006Applicant: Alstom Technology Ltd.Inventors: Shailandra Naik, Sacha Parneix, Ulrich Rathmann, Helene Saxer-Felici, Stefan Schlechtriem, Beat Von Arx
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Publication number: 20060177310Abstract: A cooled blade or vane for a gas turbine has a main blade or vane part which starts from a blade or vane root and a blade or vane shank and has a leading edge and a trailing edge, as well as, inside the main blade or vane part, a plurality of cooling ducts, which extend in the radial direction, are connected in series in terms of flow and of which a first cooling duct has a main stream of a cooling medium flowing through it along the leading edge. A second cooling duct has a main stream of a cooling medium flowing through it along the trailing edge, from the blade or vane root to the tip of the main blade or vane part. The outlet of the first cooling duct is in communication, via a first diverting region, a third cooling duct arranged between the first and second cooling ducts, and a second diverting region, with the inlet of the second cooling duct.Type: ApplicationFiled: January 12, 2006Publication date: August 10, 2006Applicant: ALSTOM Technology LtdInventors: Shailendra Naik, Sacha Parneix, Ulrich Rathmann, Helene Saxer-Felici, Stefan Schlechtriem, Beat Von Arx