Patents by Inventor Muzaffer Sutcu
Muzaffer Sutcu 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: 20220195943Abstract: A sealing assembly positioned between a first component having a first interface and a second component having a second interface is provided. The sealing assembly includes a flat bracket fixedly attached to the first interface to define an extension and a floating seal including a body portion, a first U-shaped channel arranged to engage the extension, and a second U-shaped channel inhibiting movement of the floating seal in an axial direction while allowing movement in a radial direction, and the second U-shaped channel allowing movement in the axial direction and inhibiting movement in the radial direction.Type: ApplicationFiled: December 17, 2020Publication date: June 23, 2022Inventors: Dustin C. Boudin, Jordan Metz, Johan Hsu, Muzaffer Sutcu, Robert H. Bartley, Wojciech Dyszkiewicz
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Patent number: 11359547Abstract: A sealing assembly positioned between a first component having a first interface and a second component having a second interface is provided. The sealing assembly includes a flat bracket fixedly attached to the first interface to define an extension and a floating seal including a body portion, a first U-shaped channel arranged to engage the extension, and a second U-shaped channel inhibiting movement of the floating seal in an axial direction while allowing movement in a radial direction, and the second U-shaped channel allowing movement in the axial direction and inhibiting movement in the radial direction.Type: GrantFiled: December 17, 2020Date of Patent: June 14, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Dustin C. Boudin, Jordan Metz, Johan Hsu, Muzaffer Sutcu, Robert H. Bartley, Wojciech Dyszkiewicz
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Patent number: 9163837Abstract: A combustor in a gas turbine includes a liner having an interior volume defining a main combustion zone, a fuel injection system for delivering fuel into the main combustion zone, and a flow sleeve that defines, with the liner, a passageway for air to flow on its way to be mixed with fuel from the fuel injection system, wherein the mixture is burned in the main combustion zone to create hot combustion gases. The combustor further includes a flow conditioner including at least one panel having a configuration such that air is able to pass through the panel(s) on its way to the passageway, wherein at least a substantial portion of the air that enters the passageway for being burned in the main combustion zone passes through the panel(s).Type: GrantFiled: February 27, 2013Date of Patent: October 20, 2015Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Muzaffer Sutcu, John M. Crane, Mouna Lamnaouer
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Patent number: 9151171Abstract: A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat shield may be positioned downstream from a combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall. The stepped inlet ring may be coupled to the transition section and may extend upstream from the transition section. An upstream end of the stepped inlet ring may be positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring overlaps a portion of the combustor basket. A spring clip may be positioned between the combustor basket and the stepped inlet ring such that the spring clip seals at least a portion of a gap between the combustor basket and the stepped inlet ring.Type: GrantFiled: August 27, 2010Date of Patent: October 6, 2015Assignee: SIEMENS ENERGY, INC.Inventors: Muzaffer Sutcu, Timothy A. Fox, William R. Ryan
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Patent number: 9140193Abstract: An improved gas turbine igniter (10) is provided. Turbine igniter (10) may include a guide tube (14). An igniter rod (12) may be disposed in the guide tube and extend from a hot-end region (16) to a cold-end region (18). A piston (20) may be connected to igniter rod (12). A cap (22) may be connected to guide tube (14). Cap (22) defines an access passageway (24) to the igniter rod. Structure (50) is arranged to reduce a range of radial movement of igniter rod (12) in the access passageway.Type: GrantFiled: May 3, 2011Date of Patent: September 22, 2015Assignee: SIEMENS ENERGY, INC.Inventors: Muzaffer Sutcu, Ulrich Woerz
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Patent number: 9038393Abstract: A fuel gas cooling system for a combustion basket spring clip seal support is disclosed. The fuel gas cooling system may be formed from one or more fuel gas supply channels terminating proximate to a spring clip at the intersection between a combustor basket and a transition section such that fuel gas may be supplied to the hot gas path proximate to the intersection between the combustor basket and the transition section. The fuel gas supply channel may create an intermediate fuel gas burn at this intersection, which may reduce the firing temperature at the fuel nozzles and reduce NOx emissions.Type: GrantFiled: August 27, 2010Date of Patent: May 26, 2015Assignee: SIEMENS ENERGY, INC.Inventors: Samer P. Wasif, Muzaffer Sutcu, Walter R. Laster
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Publication number: 20140238029Abstract: A combustor in a gas turbine includes a liner having an interior volume defining a main combustion zone, a fuel injection system for delivering fuel into the main combustion zone, and a flow sleeve that defines, with the liner, a passageway for air to flow on its way to be mixed with fuel from the fuel injection system, wherein the mixture is burned in the main combustion zone to create hot combustion gases. The combustor further includes a flow conditioner including at least one panel having a configuration such that air is able to pass through the panel(s) on its way to the passageway, wherein at least a substantial portion of the air that enters the passageway for being burned in the main combustion zone passes through the panel(s).Type: ApplicationFiled: February 27, 2013Publication date: August 28, 2014Inventors: Muzaffer Sutcu, John M. Crane, Mouna Lamnaouer
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Patent number: 8720204Abstract: A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator.Type: GrantFiled: February 9, 2011Date of Patent: May 13, 2014Assignee: Siemens Energy, Inc.Inventors: Reinhard Schilp, Muzaffer Sutcu
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Patent number: 8511972Abstract: A seal member for use in a channel between a transition seal structure and a vane seal structure in a gas turbine engine. The seal member includes a spring member and a sheathing assembly. A first end of the spring member is affixed to either the transition seal structure or the vane seal structure. The second end is free to move within the channel. The sheathing assembly includes a main body and a plate portion. The main body surrounds the spring member and is affixed to the second end thereof. The plate portion extends from the main body and is adapted to extend toward the other of the transition seal structure and the vane seal structure. The spring member provides a bias on the sheathing assembly such that the plate portion engages the other of the transition seal structure and the vane seal structure to limit leakage through the channel.Type: GrantFiled: December 16, 2009Date of Patent: August 20, 2013Assignee: Siemens Energy, Inc.Inventor: Muzaffer Sutcu
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Patent number: 8491259Abstract: A seal apparatus in a gas turbine engine between a transition duct and a vane structure in a first row vane assembly. The seal apparatus includes a transition seal structure associated with the transition duct and a vane seal structure associated with the vane structure. The transition seal structure includes a transition base portion that defines a first axially facing surface, a first transition lip member extending axially from the first axially facing surface, and a second transition lip member radially spaced from the first transition lip member and extending axially from the first axially facing surface. The vane seal structure includes a vane base portion that defines a second axially facing surface, a first vane lip member extending axially from the second axially facing surface, and a second vane lip member radially spaced from the first vane lip member and extending axially from the second axially facing surface.Type: GrantFiled: August 26, 2009Date of Patent: July 23, 2013Assignee: Siemens Energy, Inc.Inventor: Muzaffer Sutcu
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Publication number: 20120279195Abstract: An improved gas turbine igniter (10) is provided. Turbine igniter (10) may include a guide tube (14). An igniter rod (12) may be disposed in the guide tube and extend from a hot-end region (16) to a cold-end region (18). A piston (20) may be connected to igniter rod (12). A cap (22) may be connected to guide tube (14). Cap (22) defines an access passageway (24) to the igniter rod. Structure (50) is arranged to reduce a range of radial movement of igniter rod (12) in the access passageway.Type: ApplicationFiled: May 3, 2011Publication date: November 8, 2012Inventors: Muzaffer Sutcu, Ulrich Woerz
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Publication number: 20120198854Abstract: A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator.Type: ApplicationFiled: February 9, 2011Publication date: August 9, 2012Inventors: Reinhard Schilp, Muzaffer Sutcu
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Publication number: 20120047910Abstract: A hot gas path system for a gas turbine including a stepped inlet ring at an intersection between a downstream end of a combustor basket and an upstream end of a transition is disclosed. The heat shield may be positioned downstream from a combustor basket and proximate to an intersection between the collar and the axially extending cylindrical wall. The stepped inlet ring may be coupled to the transition section and may extend upstream from the transition section. An upstream end of the stepped inlet ring may be positioned radially outward from the combustor basket such that at least a portion of the stepped inlet ring overlaps a portion of the combustor basket. A spring clip may be positioned between the combustor basket and the stepped inlet ring such that the spring clip seals at least a portion of a gap between the combustor basket and the stepped inlet ring.Type: ApplicationFiled: August 27, 2010Publication date: March 1, 2012Inventors: Muzaffer Sutcu, Timothy A. Fox, William R. Ryan
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Publication number: 20120047904Abstract: A fuel gas cooling system for a combustion basket spring clip seal support is disclosed. The fuel gas cooling system may be formed from one or more fuel gas supply channels terminating proximate to a spring clip at the intersection between a combustor basket and a transition section such that fuel gas may be supplied to the hot gas path proximate to the intersection between the combustor basket and the transition section. The fuel gas supply channel may create an intermediate fuel gas burn at this intersection, which may reduce the firing temperature at the fuel nozzles and reduce NOx emissions.Type: ApplicationFiled: August 27, 2010Publication date: March 1, 2012Inventors: Samer P. Wasif, Muzaffer Sutcu, Walter R. Laster
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Publication number: 20110140370Abstract: A seal member for use in a channel between a transition seal structure and a vane seal structure in a gas turbine engine. The seal member includes a spring member and a sheathing assembly. A first end of the spring member is affixed to either the transition seal structure or the vane seal structure. The second end is free to move within the channel. The sheathing assembly includes a main body and a plate portion. The main body surrounds the spring member and is affixed to the second end thereof. The plate portion extends from the main body and is adapted to extend toward the other of the transition seal structure and the vane seal structure. The spring member provides a bias on the sheathing assembly such that the plate portion engages the other of the transition seal structure and the vane seal structure to limit leakage through the channel.Type: ApplicationFiled: December 16, 2009Publication date: June 16, 2011Inventor: Muzaffer Sutcu
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Publication number: 20110049812Abstract: A seal apparatus in a gas turbine engine between a transition duct and a vane structure in a first row vane assembly. The seal apparatus includes a transition seal structure associated with the transition duct and a vane seal structure associated with the vane structure. The transition seal structure includes a transition base portion that defines a first axially facing surface, a first transition lip member extending axially from the first axially facing surface, and a second transition lip member radially spaced from the first transition lip member and extending axially from the first axially facing surface. The vane seal structure includes a vane base portion that defines a second axially facing surface, a first vane lip member extending axially from the second axially facing surface, and a second vane lip member radially spaced from the first vane lip member and extending axially from the second axially facing surface.Type: ApplicationFiled: August 26, 2009Publication date: March 3, 2011Inventor: Muzaffer Sutcu