Patents by Inventor Sergei Riazantsev
Sergei Riazantsev 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: 11105205Abstract: A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.Type: GrantFiled: July 25, 2014Date of Patent: August 31, 2021Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Steffen Holzhaeuser, Daniel Eckhardt, Sergei Riazantsev, Torsten Winge
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Patent number: 10724382Abstract: A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.Type: GrantFiled: August 12, 2016Date of Patent: July 28, 2020Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Sergei Riazantsev, Stefan Rofka, Robert Marmilic, Hanspeter Knopfel, Sergey Shchukin
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Publication number: 20170044909Abstract: A gas turbine having a compressor, a combustor downstream from the compressor in a gas flow direction, and a turbine downstream from the combustor in the gas flow direction is described herein. The turbine includes a rotating part and a stationary part arranged around the rotating part. A gap between the rotating part and the stationary part, extends in a substantially radial direction relative to the rotation axis of the rotating part. A cooling fluid flows from the compressor to the gap, wherein at least a part of the cooling path extends in the stationary part, and wherein a pre-swirl nozzle is arranged adjacent to the gap and within the cooling path in the stationary part.Type: ApplicationFiled: August 12, 2016Publication date: February 16, 2017Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Sergei RIAZANTSEV, Stefan ROFKA, Robert MARMILIC, Hanspeter KNÖPFEL, Sergey SHCHUKIN
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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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Patent number: 8979470Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.Type: GrantFiled: August 4, 2011Date of Patent: March 17, 2015Assignee: Alstom Technology Ltd.Inventors: Sergei Riazantsev, Holger Kiewel, Sven Olmes, Thomas Kramer, Sergey Shchukin
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Publication number: 20150050160Abstract: A rotor shaft adapted to rotate about a rotor axis thereof. The rotor shaft includes a rotor cavity configured concentrically to the rotor axis inside the rotor shaft. The rotor shaft further includes a plurality of cooling bores extending radially outward from the rotor cavity to feed cooling air into an internal cooling system in a blade. Each cooling bore includes a bore inlet portion and a distal bore outlet portion. The respective bore inlet portion ends in a plateau, projecting above the outer circumference contour of the rotor cavity. Thus, cooling bore inlets are shifted to a low stress area and the lifetime of the rotor is improved.Type: ApplicationFiled: July 25, 2014Publication date: February 19, 2015Inventors: Steffen HOLZHAEUSER, Daniel ECKHARDT, Sergei RIAZANTSEV, Torsten WINGE
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Patent number: 8920110Abstract: The disclosure relates to a hollow gas turbine vane that is cooled by an arrangement configured to sequential cooling an endwall of the vane and its airfoil and, at the same time, the two endwalls of the vane. This arrangement can reduce cooling air demand, which can have a positive effect on the turbines efficiency.Type: GrantFiled: May 19, 2010Date of Patent: December 30, 2014Assignee: Alstom Technology Ltd.Inventors: Jose Anguisola McFeat, Erich Kreiselmaier, Christoph Nagler, Sergei Riazantsev
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Patent number: 8764395Abstract: The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.Type: GrantFiled: March 24, 2011Date of Patent: July 1, 2014Assignee: Alstom Technology Ltd.Inventors: Thomas Wilhelm, Caroline Marchmont, Sergei Riazantsev
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Patent number: 8727720Abstract: The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.Type: GrantFiled: June 30, 2010Date of Patent: May 20, 2014Assignee: Alstom Technology LtdInventors: Christoph Nagler, Jose Anguisola McFeat, Sergei Riazantsev, Marcel Koenig, Erich Kreiselmaier
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Patent number: 8523526Abstract: A blade for a gas turbine, is provided and includes a blade airfoil which extends in a blade longitudinal direction and at the lower end merges into a shank which terminates in a blade root for fastening the blade on a blade carrier, particularly on a rotor disk. Devices for cooling the blade, which are supplied with a cooling medium, especially cooling air, via a feed hole arranged on the shank at the side, are arranged inside the blade airfoil. In the region of the feed hole provision is made for a planar stiffening element which reaches beyond the immediate region of the feed hole for reducing peaks of mechanical stress.Type: GrantFiled: May 25, 2011Date of Patent: September 3, 2013Assignee: Alstom Technology LtdInventors: Sergei Riazantsev, Thomas Wilhelm
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Patent number: 8360725Abstract: A cooling passage arrangement is provided inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium. The flow region is divided in the flow direction into two cooling passages by at least one rib line which is connected to the two cast-part walls. At least one gap is provided along the at least one rib line. At the least one gap, two rib ends are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section”.Type: GrantFiled: September 29, 2010Date of Patent: January 29, 2013Assignee: Alstom Technology LtdInventors: Jose Ma Anguisola McFeat, Erich Kreiselmaier, Christoph Nagler, Sergei Riazantsev
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Patent number: 8142143Abstract: A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud.Type: GrantFiled: September 17, 2010Date of Patent: March 27, 2012Assignee: Alstom Technology Ltd.Inventors: Erich Kreiselmaier, Jose Anguisola McFeat, Christoph Nagler, Sergei Riazantsev, Brian Kenneth Wardle
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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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Publication number: 20120036864Abstract: A gas turbine engine includes a compressor with rotor blades having roots connected into seats of a compressor drum. The rotor blade roots and/or the compressor drum have longitudinal passages for a cooling fluid, connecting higher pressure areas to lower pressure areas of the gas turbine engine.Type: ApplicationFiled: August 4, 2011Publication date: February 16, 2012Applicant: ALSTOM Technology LtdInventors: Sergei RIAZANTSEV, Holger Kiewel, Sven Olmes, Thomas Kramer, Sergey Shchukin
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Publication number: 20110268582Abstract: A blade for a gas turbine, is provided and includes a blade airfoil which extends in a blade longitudinal direction and at the lower end merges into a shank which terminates in a blade root for fastening the blade on a blade carrier, particularly on a rotor disk. Devices for cooling the blade, which are supplied with a cooling medium, especially cooling air, via a feed hole arranged on the shank at the side, are arranged inside the blade airfoil. In the region of the feed hole provision is made for a planar stiffening element which reaches beyond the immediate region of the feed hole for reducing peaks of mechanical stress.Type: ApplicationFiled: May 25, 2011Publication date: November 3, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Sergei RIAZANTSEV, Thomas WILHELM
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Publication number: 20110236223Abstract: A blade for a gas turbine includes an airfoil extending in a longitudinal direction and extending transversely to the longitudinal direction between a leading edge and a trailing edge. The airfoil has a pressure side, a suction side, and a slot-like cooling medium outlet extending along the trailing edge. The cooling medium outlet is configured to discharge cooling medium supplied from an inner space of the blade. A platform extends transversely to the longitudinal direction. An end of the airfoil merges into an underside of the platform and has a transition from the airfoil to the platform at the trailing edge of the airfoil that increases in thickness in a direction toward the underside of the platform. The cooling medium outlet extends into the platform so as to reduce an operating temperature in a region of the transition from the blade airfoil to the platform.Type: ApplicationFiled: March 30, 2011Publication date: September 29, 2011Applicant: ALSTOM TECHNOLOGY LTDInventors: Christoph Nagler, Erich Kreiselmaier, Jose McFeat Anguisola, Sergei Riazantsev
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Publication number: 20110223036Abstract: The blade for a gas turbine includes a blade airfoil having a leading edge and a trailing edge and extending in the blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment, wherein on the shroud segment a first rib, projecting upwards, is arranged in the flow direction, extending transversely to the flow direction, and upstream of the first rib, in the region of the leading edge of the blade airfoil, a winglet is formed on the shroud segment for guiding of the hot gas flow in this region. With such a blade, a longer service life is achieved by provision being made for direct cooling of the winglet.Type: ApplicationFiled: March 24, 2011Publication date: September 15, 2011Applicant: Alstom Technology Ltd.Inventors: Thomas Wilhelm, Caroline Marchmont, Sergei Riazantsev
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Publication number: 20110070089Abstract: A stator blade for a gas turbine includes a blade airfoil extending in a longitudinal direction of the blade and is delimited by leading and trailing edges. The stator blade includes a shroud, whose inner side is exposed to hot gas which flows through the gas turbine. A hook-like fastening element for fastening the stator blade on a casing of the gas turbine projects outwards in the region of the trailing edge. The fastening element has a locating slot above the trailing edge for fixing a heat shield, which is connected to the shroud in the flow direction of the hot gas. A cavity is provided on the shroud between the locating slot for the heat shield and the trailing edge of the blade airfoil for reducing the thermal and mechanical stresses in the region of transition between the trailing edge and shroud, thereby extending the service life of the stator blade.Type: ApplicationFiled: September 17, 2010Publication date: March 24, 2011Applicant: ALSTOM Technology LtdInventors: Erich Kreiselmaier, Jose Anguisola McFeat, Christoph Nagler, Sergei Riazantsev, Brian Kenneth Wardle
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Publication number: 20110064585Abstract: Described is a cooling passage arrangement inside a hollow-cast cast part, with a flow region, delimited by at least two spaced apart cast-part walls, for a cooling medium (K), which flow region is divided in the flow direction into two cooling passages (7) by at least one rib line (6) which is connected to the two cast-part walls. The invention is characterized in that provision is made along the at least one rib line (6) for at least one gap (13), at which two rib ends (61, 62) are oppositely disposed a distance apart, of which one rib end has a contour in the style of a “wish bone -“Y”-cross-section” (14).Type: ApplicationFiled: September 29, 2010Publication date: March 17, 2011Applicant: ALSTOM Technology LtdInventors: Jose Ma Anguisola Mcfeat, Erich Kreiselmaier, Christoph Nagler, Sergei Riazantsev
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Publication number: 20110014054Abstract: The guide vane of a gas turbine comprises a blade having an outer platform connectable to a guide vane carrier or gas turbine casing, and at the opposite end an inner platform that carries a cover plate. The inner platform has a dovetail housing to which the cover plate is connected. The method for replacing the cover plate consists in separating the cover plate from the inner platform by cutting along the profile of the dovetail housing, then making the cover plate to slide out of the dovetail housing, thus inserting a new or refurbished cover plate into the dovetail housing.Type: ApplicationFiled: June 30, 2010Publication date: January 20, 2011Applicant: ALSTOM Technology LtdInventors: Christoph NAGLER, Jose Anguisola Mc Feat, Sergei Riazantsev, Marcel Koenig, Erich Kreiselmaier