Patents by Inventor Yevgeniy Shteyman
Yevgeniy 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: 20130269352Abstract: A gas-turbine burner having a plurality of main swirl generators which each have an inlet flow opening formed by the main swirl generator edge is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.Type: ApplicationFiled: December 14, 2012Publication date: October 17, 2013Inventors: Robert Angel, Drew Ehlert, Matthias Hase, Michael Huth, James Marshall, Yevgeniy Shteyman
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Publication number: 20130149107Abstract: A gas turbine engine including an outer case extending circumferentially around the central longitudinal axis. A cooling channel is associated with the outer surface of the outer case, the cooling channel having a channel inlet and a channel outlet. An air duct is provided including an inlet end in fluid communication with the channel outlet and an outlet end in fluid communication with an exhaust gas flow from a turbine section of the gas turbine engine. An exit structure is located at the air duct outlet end, and the exit structure provides a sub-ambient pressure at the air duct outlet end to induce a flow from the air duct inlet end to the air duct outlet end.Type: ApplicationFiled: January 22, 2013Publication date: June 13, 2013Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
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Publication number: 20130149121Abstract: An attachment system for attaching at least one exhaust diffuser downstream from a turbine assembly in a gas turbine engine is disclosed. The attachment system may include at least one attachment flange extending from a downstream edge and attached to a spring plate diffuser support structure and at least one attachment flange extending from side edges of the exhaust diffuser to couple sections of the exhaust diffuser together. The diffuser may also include a thermal barrier/cooling system for controlling a temperature of an outer case of the gas turbine engine. The thermal barrier/cooling system may form a flow path for an ambient air flow cooling.Type: ApplicationFiled: January 22, 2013Publication date: June 13, 2013Inventors: Mrinal Munshi, John W. Finneran, Yevgeniy Shteyman, Daryl J. Graber, Matthew R. Porter, Jonathan M. Leagon
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Publication number: 20130149120Abstract: A thermal barrier/cooling system for controlling a temperature of an outer case of a gas turbine engine. The thermal barrier/cooling system includes an internal insulating layer supported on an inner case surface, the internal insulating layer extending circumferentially along the inner case surface and providing a thermal resistance to radiated energy from structure located radially inwardly from the outer case. The thermal barrier/cooling system further includes a convective cooling channel defined by a panel structure located in radially spaced relation to an outer case surface of the outer case and extending around the circumference of the outer case surface. The convective cooling channel forms a flow path for an ambient air flow cooling the outer case surface.Type: ApplicationFiled: December 8, 2011Publication date: June 13, 2013Inventors: Mrinal Munshi, John Finneran, Ching-Pang Lee, Yevgeniy Shteyman, Daryl Graber, Matthew R. Porter, Jonathan M. Leagon
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Patent number: 8387394Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.Type: GrantFiled: July 2, 2008Date of Patent: March 5, 2013Assignee: Siemens AktiengesellschaftInventors: Matthias Hase, Michael Huth, Robert Angel, Drew Ehlert, James Marshall, Yevgeniy Shteyman
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Publication number: 20120023968Abstract: A flange connection for an exhaust section of a gas turbine engine. The flange connection includes a stub flange attached to an exhaust manifold. The stub flange has a first axial face for engagement with the axial face of a cylinder flange extending radially from an exhaust cylinder. A plate structure attached to the cylinder flange is configured to provide axial retention of the stub flange to the axial face of the cylinder flange. The plate structure includes a resilient beam portion extending radially inwardly and engaging a second axial face of the stub flange. The stub flange is retained between the cylinder flange and the beam portion of the plate structure in an interference fit to provide three degrees of freedom of the stub flange relative to the exhaust cylinder.Type: ApplicationFiled: March 11, 2011Publication date: February 2, 2012Inventors: Yevgeniy Shteyman, James Marshall, Brian Micklos, Jonathan Leagon, Christopher Scogin, Brian H. Terpos, Robert T. Brooks, Scott Smith, Robert W. Spitzer, David Wiebe
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Publication number: 20120020770Abstract: A gas turbine includes a casing, a first diaphragm assembly, a second diaphragm assembly, and first energy absorbing apparatus. The casing has a radially outer surface and a radially inner surface including an annular slot extending circumferentially therein. The first diaphragm assembly includes a first inner structure, a first outer structure and a plurality of airfoils extending between the first inner and outer structures. The second diaphragm assembly includes a second inner structure, a second outer structure and a plurality of airfoils extending between the second inner and outer structures. The first energy absorbing apparatus engages a first end portion of the first outer structure so as to absorb at least portions of unsteady aerodynamic loads and steady rotational loads generated by the first diaphragm assembly.Type: ApplicationFiled: July 22, 2010Publication date: January 26, 2012Inventors: Friedrich Rogers, Yevgeniy Shteyman
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Patent number: 8079804Abstract: A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage.Type: GrantFiled: September 18, 2008Date of Patent: December 20, 2011Assignee: Siemens Energy, Inc.Inventors: Yevgeniy Shteyman, Frank Tsai, James F. Marshall, Scott W. Smith
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Publication number: 20100275605Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.Type: ApplicationFiled: July 2, 2008Publication date: November 4, 2010Inventors: Matthias Hase, Michael Huth, Robert Angel, Drew Ehlert, James Marshall, Yevgeniy Shteyman
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Patent number: 7798768Abstract: A turbine vane ID support system usable to support the ID of a turbine vane and including a transition seal system and a turbine vane ID forward rail seal system. The transition seal system may seal the turbine vane ID support body to a transition, and the turbine vane ID forward rail seal system may seal the turbine vane ID support body to a turbine vane. Use of the transition seal system and the turbine vane ID forward rail seal system eliminates the problems inherent with conventional seals used to seal transitions directly to turbine vanes. The turbine vane ID support system may also be configured such that the turbine vane ID support system may be removed to facilitate removal of turbine vanes and blades for repair or replacement.Type: GrantFiled: October 25, 2006Date of Patent: September 21, 2010Assignee: Siemens Energy, Inc.Inventors: John Strain, Yevgeniy Shteyman, Robert W. Spitzer
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Patent number: 7762766Abstract: A support for the first row turbine vanes (12) in a gas turbine engine, the support including a support framework (18). The support framework (18) includes an outer vane carrier (34), and an inner vane carrier (36) connected to the outer vane carrier (34) by a plurality of struts (44, 46). The outer vane carrier (34) is mounted to an inner casing (16) of the engine and the struts (44, 46) support the inner vane carrier (36) in cantilevered relation to the outer vane carrier (34). An aft outer flange (94) of each first row vane (12) is supported on the outer vane carrier (34) and a forward inner flange (114) of the vane (12) is support on the inner vane carrier (36).Type: GrantFiled: July 6, 2006Date of Patent: July 27, 2010Assignee: Siemens Energy, Inc.Inventors: Yevgeniy Shteyman, John Strain, William R. Ryan, Robert W. Spitzer
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Publication number: 20100068043Abstract: A gas turbine case is provided including an outer case surface, and a channel portion formed as a recessed area extending radially inwardly into the outer case surface. The channel portion extends about a circumference of the case. An outer flow jacket is attached to the outer case surface and extends over the channel portion to define an enclosed cooling passage along the outer case surface. At least one inlet passage and at least one outlet passage are provided in fluid communication with the enclosed cooling passage to convey air to and from the cooling passage.Type: ApplicationFiled: September 18, 2008Publication date: March 18, 2010Inventors: Yevgeniy Shteyman, Frank Tsai, James F. Marshall, Scott W. Smith
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Patent number: 7435058Abstract: A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.Type: GrantFiled: January 18, 2005Date of Patent: October 14, 2008Assignee: Siemens Power Generation, Inc.Inventors: Christian X. Campbell, Harry A. Albrecht, Yevgeniy Shteyman, Jay A. Morrison
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Publication number: 20080181766Abstract: A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.Type: ApplicationFiled: January 18, 2005Publication date: July 31, 2008Inventors: Christian X. Campbell, Harry A. Albrecht, Yevgeniy Shteyman, Jay A. Morrison
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Publication number: 20080101927Abstract: A turbine vane ID support system usable to support the ID of a turbine vane and including a transition seal system and a turbine vane ID forward rail seal system. The transition seal system may seal the turbine vane ID support body to a transition, and the turbine vane ID forward rail seal system may seal the turbine vane ID support body to a turbine vane. Use of the transition seal system and the turbine vane ID forward rail seal system eliminates the problems inherent with conventional seals used to seal transitions directly to turbine vanes. The turbine vane ID support system may also be configured such that the turbine vane ID support system may be removed to facilitate removal of turbine vanes and blades for repair or replacement.Type: ApplicationFiled: October 25, 2006Publication date: May 1, 2008Inventors: John Strain, Yevgeniy Shteyman, Robert W. Sptizer
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Patent number: 7326030Abstract: A turbine airfoil support system for coupling together a turbine airfoil formed from two or more components, wherein the support system is particularly suited for use with a composite airfoil. In at least one embodiment, the turbine airfoil support system may be configured to attach shrouds to both ends of an airfoil and to maintain a compressive load on those shrouds while the airfoil is positioned in a turbine engine. Application of the compressive load to the airfoil increases the airfoil's ability to withstand tensile forces encountered during turbine engine operation.Type: GrantFiled: February 2, 2005Date of Patent: February 5, 2008Assignee: Siemens Power Generation, Inc.Inventors: Harry A. Albrecht, Yevgeniy Shteyman
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Publication number: 20080008584Abstract: A support for the first row turbine vanes (12) in a gas turbine engine, the support including a support framework (18). The support framework (18) includes an outer vane carrier (34), and an inner vane carrier (36) connected to the outer vane carrier (34) by a plurality of struts (44, 46). The outer vane carrier (34) is mounted to an inner casing (16) of the engine and the struts (44, 46) support the inner vane carrier (36) in cantilevered relation to the outer vane carrier (34). An aft outer flange (94) of each first row vane (12) is supported on the outer vane carrier (34) and a forward inner flange (114) of the vane (12) is support on the inner vane carrier (36).Type: ApplicationFiled: July 6, 2006Publication date: January 10, 2008Inventors: Yevgeniy Shteyman, John Strain, William R. Ryan, Robert W. Spitzer
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Patent number: 7258530Abstract: An airfoil (44) formed of a plurality of pre-fired structural CMC panels (46, 48, 50, 52). Each panel is formed to have an open shape having opposed ends (54) that are free to move during the drying, curing and/or firing of the CMC material in order to minimize interlaminar stresses caused by anisotropic sintering shrinkage. The panels are at least partially pre-shrunk prior to being joined together to form the desired structure, such as an airfoil (42) for a gas turbine engine. The panels may be joined together using a backing member (30), using flanged ends (54) and a clamp (56), and/or with a bond material (36), for example.Type: GrantFiled: January 21, 2005Date of Patent: August 21, 2007Assignee: Siemens Power Generation, Inc.Inventors: Jay A. Morrison, Gary B. Merrill, Steven James Vance, Harry A. Albrecht, Yevgeniy Shteyman
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Patent number: 7255535Abstract: Embodiments of the invention relate to various cooling systems for a turbine vane made of stacked ceramic matrix composite (CMC) laminates. Each airfoil-shaped laminate has an in-plane direction and a through thickness direction substantially normal to the in-plane direction. The laminates have anisotropic strength characteristics in which the in-plane tensile strength is substantially greater than the through thickness tensile strength. Such a vane construction lends itself to the inclusion of various cooling features in individual laminates using conventional manufacturing and forming techniques. When assembled in a radial stack, the cooling features in the individual laminates can cooperate to form intricate three dimensional cooling systems in the vane.Type: GrantFiled: December 2, 2004Date of Patent: August 14, 2007Inventors: Harry A. Albrecht, Yevgeniy Shteyman, Steven James Vance, Jay A. Morrison
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Patent number: 7247002Abstract: A component (10) for a gas turbine engine formed of a stacked plurality of ceramic matrix composite (CMC) lamellae (12) supported by a metal support structure (20). Individual lamellae are supported directly by the support structure via cooperating interlock features (30, 32) formed on the lamella and on the support structure respectively. Mating load-transferring surfaces (34, 36) of the interlock features are disposed in a plane (44) oblique to local axes of thermal growth (38, 40) in order to accommodate differential thermal expansion there between with delta alpha zero expansion (DAZE). Reinforcing fibers (62) within the CMC material may be oriented in a direction optimized to resist forces being transferred through the interlock features. Individual lamellae may all have the same structure or different interlock feature shapes and/or locations may be used in different groups of the lamellae. Applications for this invention include an airfoil assembly (10) and a ring segment assembly (82).Type: GrantFiled: June 29, 2005Date of Patent: July 24, 2007Assignee: Siemens Power Generation, Inc.Inventors: Harry A. Albrecht, Yevgeniy Shteyman, Jay A. Morrison, Daniel G. Thompson