Patents by Inventor Sergey Vorontsov
Sergey Vorontsov 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: 10450885Abstract: A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. In use, a vortex is created in the cavity.Type: GrantFiled: January 25, 2017Date of Patent: October 22, 2019Assignee: ANSALDO ENERGIA SWITZERLAND AGInventors: Andrey Sedlov, Maxim Plodistyy, Sergey Vorontsov
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Publication number: 20170211405Abstract: A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. In use, a vortex is created in the cavity.Type: ApplicationFiled: January 25, 2017Publication date: July 27, 2017Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Andrey SEDLOV, Maxim PLODISTYY, Sergey VORONTSOV
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Patent number: 8182210Abstract: A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.Type: GrantFiled: December 23, 2009Date of Patent: May 22, 2012Assignee: ALSTOM Technology LtdInventors: Alexander Khanin, Igor Kurganov, Sergey Vorontsov, Anatoly Shunin
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Patent number: 8152454Abstract: A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.Type: GrantFiled: December 23, 2009Date of Patent: April 10, 2012Assignee: Alstom Technology LtdInventors: Alexander Khanin, Igor Kurganov, Sergey Vorontsov, Victor Odinokov
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Patent number: 8105024Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.Type: GrantFiled: September 24, 2008Date of Patent: January 31, 2012Assignee: Alstom Technology LtdInventors: Alexander Khanin, Arkadi Fokine, Maxim Konter, Sergey Vorontsov
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Patent number: 8052382Abstract: A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of heat shield elements (12), and with a stator (3) which has a stator blade row (8), with a plurality of stator blades (9), which is arranged axially between the two adjacent rotor blade rows (5). The stator blades (9) have a stator sealing structure (10) radially on the inside. The heat shield elements (12) have a rotor sealing structure (13) radially on the outside which interacts with the stator sealing structure (10) for forming an axial seal (14). Furthermore, a blade radial seal (15) is formed between two adjacent rotor blades (6), and also a heat shield radial seal (16) is formed between two adjacent heat shield elements (12), and in each case separates a gas path (17) from the rotor (2).Type: GrantFiled: June 19, 2009Date of Patent: November 8, 2011Assignee: ALSTOM Technology Ltd.Inventors: Maxim Konter, Alexander Khanin, Alexander Burmistrov, Sergey Vorontsov
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Patent number: 8043052Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).Type: GrantFiled: October 26, 2009Date of Patent: October 25, 2011Assignee: ALSTOM Technology Ltd.Inventors: Maxim Konter, Sergey Vorontsov, Alexander Khanin, Alexey Karelin, Alexander Bone
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Patent number: 7997856Abstract: A stator heat shield (6) for a gas turbine (1) includes an outside (11) which in the installed state faces a hot gas path (9) of the gas turbine (1), and an inside (12) facing away from the outside (11). A plurality of ribs (13) are formed on the inside (12) and extend axially in the installed state with regard to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate (14) is arranged on the inside (12) and is in contact with the ribs (13). At least one groove (16) is designed in an end face (15) bordering the stator heat shield (6) in the circumferential direction, into which at least one sealing element (18) can be inserted. A plurality of bores (19) are included, each opening at a distance from the groove (16) in the direction of the outside (11) at the inside (12) at one end and on the end face (15) at the other end and arranged a distance apart from one another in the axial direction.Type: GrantFiled: October 15, 2009Date of Patent: August 16, 2011Assignee: ALSTOM Technology Ltd.Inventors: Alexander Khanin, Edouard Sloutski, Sergey Vorontsov, Anton Sumin
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Publication number: 20100150710Abstract: A guide vane for a gas turbine includes a vane body having a leading edge and a trailing edge and a shroud extending at least between the leading edge and the trailing edge. The shroud has a first side wall and a second side wall extending essentially radially and in a longitudinal direction of the gas turbine. The first side wall has a groove disposed in a region of the trailing edge extending in a longitudinal direction of the shroud and is configured to receive a sealing plate. The first side wall also has a clearance extending from the groove in a region of the trailing edge, wherein a depth of the clearance in a circumferential direction of the gas turbine is equal to a depth of the groove, and wherein a width of the clearance in the longitudinal direction of the shroud is between one to three times the depth of the clearance.Type: ApplicationFiled: December 23, 2009Publication date: June 17, 2010Applicant: ALSTOM Technology LtdInventors: Alexander Khanin, Igor Kurganov, Sergey Vorontsov, Victor Odinokov
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Publication number: 20100150712Abstract: A gas turbine includes a turbine housing; a rotatable turbine rotor with turbine blades; and at least one heat shield segment for a stator. The heat shield segment is disposed radially between the rotor and the housing and attached to the housing and has a profile with a curved section in at least one region in an axial direction of the gas turbine and a radial outer surface. The heat shield segment includes a rib, a first boss, and a second boss disposed on the radial outer surface.Type: ApplicationFiled: December 23, 2009Publication date: June 17, 2010Applicant: ALSTOM Technology LtdInventors: Alexander Khanin, Igor Kurganov, Sergey Vorontsov, Anatoly Shunin
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Publication number: 20100111683Abstract: A fluid flow engine (1), in particular a turbo engine, has at least one guide vane row (5) with a plurality of guide vanes (6) and at least one rotor blade row (7) with a plurality of rotor blades (8). One guide vane row (5) and one rotor blade row (7) that follows the former directly downstream with respect to a working gas flow (11), together form a stage (10) of the fluid flow engine (1).Type: ApplicationFiled: October 26, 2009Publication date: May 6, 2010Inventors: Maxim Konter, Sergey Vorontsov, Alexander Khanin, Alexey Karelin, Alexander Bone
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Patent number: 7674088Abstract: A vane arrangement (1) of a turbo machine (4), in particular of a gas turbine, includes at least one vane carrier (2) attached to a housing (5) of a turbo machine (4), and several vanes (3) attached to the vane carrier (2) and circumferentially arranged side by side, wherein the attachment between the vane carrier (2) and respective vane (3) is adapted for being axially pluggable. In order to simplify dismounting of a single vane (3) at least one of the vanes (3) is provided with an extraction device (35) having at least one axially extending extraction through-hole (36). The respective extraction through hole (36) is provided with an inner thread (37), and the vane carrier (2) is provided with an abutment zone (38) axially opposing the extraction through hole (36).Type: GrantFiled: March 31, 2008Date of Patent: March 9, 2010Assignee: ALSTOM Technology Ltd.Inventors: Alexander Khanin, Iouri Strelkov, Sergey Vorontsov
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Publication number: 20100047062Abstract: A stator heat shield (6) for a gas turbine (1) includes an outside (11) which in the installed state faces a hot gas path (9) of the gas turbine (1), and an inside (12) facing away from the outside (11). A plurality of ribs (13) are formed on the inside (12) and extend axially in the installed state with regard to an axis of rotation (8) of a rotor (3) of the gas turbine (1) and, in the circumferential direction, are spaced a distance apart from one another. At least one baffle plate (14) is arranged on the inside (12) and is in contact with the ribs (13). At least one groove (16) is designed in an end face (15) bordering the stator heat shield (6) in the circumferential direction, into which at least one sealing element (18) can be inserted. A plurality of bores (19) are included, each opening at a distance from the groove (16) in the direction of the outside (11) at the inside (12) at one end and on the end face (15) at the other end and arranged a distance apart from one another in the axial direction.Type: ApplicationFiled: October 15, 2009Publication date: February 25, 2010Inventors: Alexander Khanin, Edouard Sloutski, Sergey Vorontsov, Anton Sumin
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Publication number: 20090274552Abstract: A gas turbine (1) includes a rotor (2) which has two rotor blade rows (5) with a plurality of rotor blades (6), and also a rotor heat shield (7), which is arranged between them, with a plurality of heat shield elements (12), and with a stator (3) which has a stator blade row (8), with a plurality of stator blades (9), which is arranged axially between the two adjacent rotor blade rows (5). The stator blades (9) have a stator sealing structure (10) radially on the inside. The heat shield elements (12) have a rotor sealing structure (13) radially on the outside which interacts with the stator sealing structure (10) for forming an axial seal (14). Furthermore, a blade radial seal (15) is formed between two adjacent rotor blades (6), and also a heat shield radial seal (16) is formed between two adjacent heat shield elements (12), and in each case separates a gas path (17) from the rotor (2).Type: ApplicationFiled: June 19, 2009Publication date: November 5, 2009Inventors: Maxim Konter, Alexander Khanin, Alexander Burmistrov, Sergey Vorontsov
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Publication number: 20090081027Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.Type: ApplicationFiled: September 24, 2008Publication date: March 26, 2009Applicant: ALSTOM Technology LtdInventors: Alexander KHANIN, Arkadi Fokine, Maxim Konter, Sergey Vorontsov
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Publication number: 20090041587Abstract: A rotating blade (1) for a gas turbine comprises an internal cooling structure having at least three cooling air passages (5, 6, 7) in fluid connection with one another by turns (9, 10). An opening (12) provides an outlet for dissolved core material to be removed from the blade following casting of the cooling structure without any residue remaining within. According to the invention, the cooling structure comprises trip strips (13, 15) in the first and second passage (5, 6) with specified ratio of height to distance between trip strips and the trip strips (13) in the first passage being arranged at 90° with respect to the direction of airflow. In a particular embodiment, the trip strips (15) in the second passage (6) are arranged at angle of 45°. The design according to the invention assures sufficient airflow through first and second air passages (5, 6).Type: ApplicationFiled: August 4, 2008Publication date: February 12, 2009Applicant: ALSTOM TECHNOLOGY LTDInventors: Maxim Konter, Anton Sumin, Sergey Vorontsov, Alexander Khanin
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Publication number: 20080193289Abstract: A vane arrangement (1) of a turbo machine (4), in particular of a gas turbine, includes at least one vane carrier (2) attached to a housing (5) of a turbo machine (4), and several vanes (3) attached to the vane carrier (2) and circumferentially arranged side by side, wherein the attachment between the vane carrier (2) and respective vane (3) is adapted for being axially pluggable. In order to simplify dismounting of a single vane (3) at least one of the vanes (3) is provided with an extraction device (35) having at least one axially extending extraction through-hole (36). The respective extraction through hole (36) is provided with an inner thread (37), and the vane carrier (2) is provided with an abutment zone (38) axially opposing the extraction through hole (36).Type: ApplicationFiled: March 31, 2008Publication date: August 14, 2008Inventors: Alexander Khanin, Iouri Strelkov, Sergey Vorontsov
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Patent number: 6857639Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics: each component (1) has one each groove (7) that is open towards the gap (3), the two grooves (7) are essentially facing each other in the gap (3), in each groove (7), a compensation body (16) is movably positioned transversely to the longitudinal groove direction and parallel to the gap plane (10), each compensation body (11) abuts the groove bottom (9) of the corresponding groove (7) in a sealing manner, each compensation body (11) has a V-shaped receiving groove (14) that is open towards the facing compensation body (11), a mutual sealing body (16) has a rhombus-shaped cross-section and projects with outer sides (17) into both receiving grooves (14), the straight inner sides (15) of each receiving groove (14) are angled towards each other at the same angle as the straight outer sides (17), in each receiving groove (14), at least one outType: GrantFiled: July 3, 2003Date of Patent: February 22, 2005Assignee: ALSTOM Technology LTDInventors: Alexander Beeck, Arkadi Fokine, Edouard Sloutski, Sergey Vorontsov
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Publication number: 20040041350Abstract: The invention relates to a gap seal (6) for sealing a gap (3) between two adjacent components (1, 2), in particular of turbo machines, with the following characteristics:Type: ApplicationFiled: July 3, 2003Publication date: March 4, 2004Inventors: Alexander Beeck, Arkadi Fokine, Edouard Sloutski, Sergey Vorontsov