Patents by Inventor Yevgeniy P. Shteyman
Yevgeniy P. Shteyman 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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Publication number: 20240068368Abstract: A turbine blade includes a platform, a blade airfoil attached to one side of the platform, a blade root attached to the other side of the platform, a manifold attached to the blade root. The blade root defines a first cooling passage and a second cooling passage. The manifold includes an outer wall, a first compartment having a first flow area defined by a first aperture formed at the outer wall, and a second compartment having a second flow area defined by a second aperture formed at the outer wall. The first compartment meters a non-zero first flow of cooling air to the first cooling passage through the first flow area. The second compartment meters a non-zero second flow of cooling air to the second cooling passage through the second flow area that is different than the first flow area.Type: ApplicationFiled: June 15, 2023Publication date: February 29, 2024Inventors: Yevgeniy P. Shteyman, Phillip W. Gravett, Stephen Williamson
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Patent number: 10208601Abstract: An air separator for a turbine engine is provided. The air separator includes an aft air separator member (10) having an annular frame (14) which defines a chamber (16) configured to engage disc shoulders (18) configured in a first stage of the turbine engine. The aft air separator member (10) is constrained from movement along a radial direction by the disc shoulders engaged in the chamber of the aft air separator member. A forward air separator member (12) is affixed at a forward end thereof to a torque tube (20) to constrain movement along the radial direction. The forward air separator includes at an aft end thereof a flange (22) that engages the aft air separator member. The forward air separator member is constrained from outward radial movement along the radial direction by way of a recess (24) constructed in a portion of the aft air separator member.Type: GrantFiled: May 5, 2014Date of Patent: February 19, 2019Assignee: SIEMENS ENERGY, INC.Inventors: Brian D. Nereim, Piyush Sane, Yevgeniy P. Shteyman
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Patent number: 10077676Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: GrantFiled: November 19, 2015Date of Patent: September 18, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Randy Tindell
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Patent number: 9988931Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: GrantFiled: April 17, 2015Date of Patent: June 5, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, John A. Orosa
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Patent number: 9840937Abstract: Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.Type: GrantFiled: January 14, 2015Date of Patent: December 12, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, Thomas Heylmun
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Patent number: 9695713Abstract: Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs.Type: GrantFiled: February 11, 2015Date of Patent: July 4, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Daniel M. Eshak, Yevgeniy P. Shteyman, John Giaimo, George J. Obranic, Jr., Sudeep Bosu
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Patent number: 9650919Abstract: A sealing arrangement for a gas turbine including exhaust and manifold diffusers separated by a circumferential diffuser gap. The sealing arrangement includes a forward clamp arrangement attached to the exhaust diffuser wherein the forward clamp arrangement includes a forward groove. The sealing arrangement also includes an aft clamp arrangement attached to manifold diffuser wherein the aft clamp arrangement includes an aft groove. Further, the sealing arrangement includes a flexible circumferential seal including forward and aft loop portions. The forward loop portion is located in the forward groove and the aft loop portion is located in the aft groove wherein the circumferential seal extends across the circumferential diffuser gap to seal the circumferential diffuser gap. The forward and aft loop portions are moveable in the forward and aft grooves to enable movement of the circumferential seal in a circumferential direction to accommodate thermal expansion of the exhaust and manifold diffusers.Type: GrantFiled: August 4, 2014Date of Patent: May 16, 2017Assignee: Siemens Energy, Inc.Inventors: Michael Whitty, Jeffrey D. Kesten, Yevgeniy P. Shteyman, Cristina Cook, Keith J. Gordon
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Patent number: 9617873Abstract: Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.Type: GrantFiled: January 14, 2015Date of Patent: April 11, 2017Assignee: SIEMENS ENERGY, INC.Inventors: Daniel M. Eshak, John Giaimo, Thomas Heylmun, Yevgeniy P. Shteyman
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Publication number: 20160208642Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A trailing edge full span flap is removable secured behind the trailing edge of the tangential strut in a fluid flow direction and extending between the outer cylindrical surface and the inner cylindrical surface where the full span flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: ApplicationFiled: November 19, 2015Publication date: July 21, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Randy Tindell
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Publication number: 20160201506Abstract: Disclosed are a casing arrangement and a method to reduce vibrations in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer.Type: ApplicationFiled: January 14, 2015Publication date: July 14, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, Thomas Heylmun
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Publication number: 20160123152Abstract: An air separator for a turbine engine is provided. The air separator includes an aft air separator member (10) having an annular frame (14) which defines a chamber (16) configured to engage disc shoulders (18) configured in a first stage of the turbine engine. The aft air separator member (10) is constrained from movement along a radial direction by the disc shoulders engaged in the chamber of the aft air separator member. A forward air separator member (12) is affixed at a forward end thereof to a torque tube (20) to constrain movement along the radial direction. The forward air separator includes at an aft end thereof a flange (22) that engages the aft air separator member. The forward air separator member is constrained from outward radial movement along the radial direction by way of a recess (24) constructed in a portion of the aft air separator member.Type: ApplicationFiled: May 5, 2014Publication date: May 5, 2016Applicant: Siemens Energy, Inc.Inventors: Brian D. Nereim, Piyush Sane, Yevgeniy P. Shteyman
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Publication number: 20160084087Abstract: A rotor for a turbine engine. The rotor may include an assembly of axially-bolted compressor disks (14). A compressor torque tube (30) is connected to the assembly of compressor disks (14). The rotor may further include an assembly of axially-bolted turbine disks (22). A turbine torque tube (32) is axially connected to the assembly of turbine disks (22). A marriage coupling (34) is arranged to interconnect the respective torque tubes (30, 32). The marriage coupling includes a flange joint arranged to decouple the compressor torque tube or the turbine torque tube so that individual and separate access can be provided to the respective assemblies of compressor disks and turbine disks.Type: ApplicationFiled: May 5, 2014Publication date: March 24, 2016Applicant: Siemens Energy, Inc.Inventors: Brian D. Nereim, Piyush Sane, Yevgeniy P. Shteyman
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Publication number: 20160076396Abstract: Disclosed are a casing arrangement and a method to reduce critical panel mode response in a gas turbine casing. The casing arrangement includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A plurality of stiffening ribs are coupled to a surface of the inner flow path which effectively increases the stiffness reducing the critical panel mode response.Type: ApplicationFiled: January 14, 2015Publication date: March 17, 2016Inventors: Daniel M. Eshak, John Giaimo, Thomas Heylmun, Yevgeniy P. Shteyman
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Publication number: 20160076397Abstract: Disclosed are a system for damping vibrations of a gas turbine exhaust and a method to damp vibrations of a gas turbine exhaust. The system includes a turbine exhaust cylinder connected to a turbine exhaust manifold establishing a fluid flow path, the fluid flow path including an inner and an outer flow path. A damping blanket damps the vibrations and is coupled to a surface of the inner flow path via a constraining layer clamped by a plurality of studs.Type: ApplicationFiled: February 11, 2015Publication date: March 17, 2016Inventors: Daniel M. Eshak, Yevgeniy P. Shteyman, John Giaimo, George J. Obranic, JR., Sudeep Bosu
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Publication number: 20160076398Abstract: A system and method to minimize flow induced vibration in a gas turbine exhaust is provided. The system includes a turbine exhaust manifold connected to a turbine exhaust cylinder establishing a fluid flow path, the fluid flow path bounded radially outward by an outer cylindrical surface and bounded radially inward by an inner cylindrical surface. At least one tangential strut is arranged between the outer cylindrical surface and the inner cylindrical surface. A first flap is arranged diagonally between the tangential strut and the outer cylindrical surface or the inner cylindrical surface where the first flap minimizes vortex shedding of the fluid flow from the tangential strut.Type: ApplicationFiled: April 17, 2015Publication date: March 17, 2016Inventors: Yevgeniy P. Shteyman, John Giaimo, Daniel M. Eshak, John A. Orosa
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Publication number: 20160032781Abstract: A sealing arrangement for a gas turbine including exhaust and manifold diffusers separated by a circumferential diffuser gap. The sealing arrangement includes a forward clamp arrangement attached to the exhaust diffuser wherein the forward clamp arrangement includes a forward groove. The sealing arrangement also includes an aft clamp arrangement attached to manifold diffuser wherein the aft clamp arrangement includes an aft groove. Further, the sealing arrangement includes a flexible circumferential seal including forward and aft loop portions. The forward loop portion is located in the forward groove and the aft loop portion is located in the aft groove wherein the circumferential seal extends across the circumferential diffuser gap to seal the circumferential diffuser gap. The forward and aft loop portions are moveable in the forward and aft grooves to enable movement of the circumferential seal in a circumferential direction to accommodate thermal expansion of the exhaust and manifold diffusers.Type: ApplicationFiled: August 4, 2014Publication date: February 4, 2016Inventors: Michael Whitty, Jeffrey D. Kesten, Yevgeniy P. Shteyman, Cristina Cook, Keith J. Gordon
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Patent number: 7093359Abstract: A method of manufacturing a composite structure uses a layer of an insulating material (22) as a mold for forming a substrate of a ceramic matrix composite (CMC) material (24). The insulating material may be formed in the shape of a cylinder (10) with the CMC material wound on an outer surface (14) of the cylinder to form a gas turbine combustor liner (20). Alternatively, the insulating material may be formed in the shape of an airfoil section (32) with the CMC material formed on an inside surface (36) of the insulating material. The airfoil section may be formed of a plurality of halves (42, 44) to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure (102) defining a hot gas flow passage (98) is manufactured by forming insulating material in the shape of opposed airfoil halves (104) joined at respective opposed ends by platform members (109).Type: GrantFiled: September 17, 2002Date of Patent: August 22, 2006Assignee: Siemens Westinghouse Power CorporationInventors: Jay A. Morrison, Gary Brian Merrill, Jay Edgar Lane, Steven C. Butner, Harry A. Albrecht, Scott M. Widrig, Yevgeniy P. Shteyman
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Patent number: 6709230Abstract: A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.Type: GrantFiled: May 31, 2002Date of Patent: March 23, 2004Assignee: Siemens Westinghouse Power CorporationInventors: Jay A. Morrison, Chris Campbell, Gary Brian Merrill, Jay Edgar Lane, Daniel George Thompson, Harry A. Albrecht, Yevgeniy P. Shteyman
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Publication number: 20030223861Abstract: A hybrid vane (50) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member (52) bonded to a substantially solid core member (54). The airfoil member and core member are cooled by a cooling fluid (58) passing through cooling passages (56) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond ((70) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation (72) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.Type: ApplicationFiled: May 31, 2002Publication date: December 4, 2003Applicant: Siemens Westinghouse Power CorporationInventors: Jay A. Morrison, Chris Campbell, Gary Brian Merrill, Jay Edgar Lane, Daniel George Thompson, Harry A. Albrecht, Yevgeniy P. Shteyman