Patents by Inventor Robert H. Bartley
Robert H. Bartley 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: 11746667Abstract: A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.Type: GrantFiled: August 6, 2020Date of Patent: September 5, 2023Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Markus Raben, Kunyuan Zhou, Wojciech Dyszkiewicz, Adam J. Weaver, Robert H. Bartley, James Bertoncello, Mahmut Faruk Aksit, Ertugrul Tolga Duran, Erdem Gorgun, Sadik Hazer, Ali Ihsan Yurddas
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Publication number: 20220389827Abstract: A seal for sealing a gap in a combustion apparatus of a gas turbine between a first side and an opposite second side. The seal includes a steel strap with a flat shape and a first metal web with a flat shape attached to the steel strap on the first side and a second metal web attached to the steel strap on the second side. Thereby the seal has a seal thickness with at least the steel strap plus the first metal web plus the thickness of the second metal web, wherein the seal thickness is at most 0.2-times of width of the seal. The new seal has an Omega shape of the second metal web, which is therefore attached on both sides with a flat shaped portion to the steel strap.Type: ApplicationFiled: August 6, 2020Publication date: December 8, 2022Applicant: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Markus Raben, Kunyuan Zhou, Wojciech Dyszkiewicz, Adam J. Weaver, Robert H. Bartley, James Bertoncello, Mahmut Faruk Aksit, Ertugrul Tolga Duran, Erdem Gorgun, Sadik Hazer, Ali Ihsan Yurddas
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Patent number: 11371368Abstract: A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.Type: GrantFiled: March 27, 2018Date of Patent: June 28, 2022Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Viraj Wadatkar, Adam J. Weaver, Robert H. Bartley
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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: 11066941Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.Type: GrantFiled: December 11, 2014Date of Patent: July 20, 2021Assignee: Siemens Energy Global GmbH & Co. KGInventors: Manish Kumar, Joseph L. Evins, Khamhou Sayavong, Matthias Hase, Miguel Bascones, Adam J. Weaver, Robert H. Bartley, Lashanda N. Williams
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Publication number: 20210054751Abstract: A sealing arrangement in a gas turbine engine to seal a gap between first and second turbine components is provided. The sealing arrangement includes a first arcuate feather seal connected to an anchoring assembly of the sealing arrangement affixed to the first turbine component. A second arcuate feather seal is affixed to the second turbine component. The first arcuate feather seal and the second arcuate feather seal are responsive to a pressure differential that develops across the gap to form a pressure-loaded sealing joint between respective sealing surfaces of the first arcuate feather seal and the second arcuate feather seal. The sealing arrangement provides substantial design flexibility since it can reliably provide appropriate sealing functionality while enabling multiple degrees of freedom, such as to accommodate radial and/or axial displacements that can develop between the first turbine component and the second turbine component.Type: ApplicationFiled: March 27, 2018Publication date: February 25, 2021Inventors: Viraj Wadatkar, Adam J. Weaver, Robert H. Bartley
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Patent number: 10704786Abstract: A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.Type: GrantFiled: January 29, 2015Date of Patent: July 7, 2020Assignee: SIEMENS ENERGY, INC.Inventors: Walter Ray Laster, Timothy A. Fox, Robert H. Bartley
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Patent number: 10443855Abstract: A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.Type: GrantFiled: October 23, 2014Date of Patent: October 15, 2019Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Vinayak V. Barve, Timothy A. Fox, Robert H. Bartley, Sachin Terdalkar
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Patent number: 10082294Abstract: A fuel injector for injecting fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) and a second fuel supply channel (20) may be coaxially arranged in a fuel delivery structure (12). A first set of vanes 22 includes a radial passage (24) in fluid communication with the first channel (18) to receive a first fuel. Passage (24) branches into passages (26) each having an aperture (28) to inject the first fuel without jet in cross-flow injection. A second set of vanes (32) includes a radial passage (34) in fluid communication with the second channel (20) to receive a second fuel. Passage (34) branches into passages (36) each having an aperture (38) arranged to inject the second fuel also without jet in cross-flow injection. This arrangement may be effective to reduce flashback that otherwise may be encountered in fuels having a relatively high flame speed.Type: GrantFiled: January 29, 2015Date of Patent: September 25, 2018Assignee: SIEMENS ENERGY, INC.Inventors: Walter Ray Laster, Jacob William Hardes, Robert H. Bartley, Mario Gaviria
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Publication number: 20180023812Abstract: A fuel injector for injecting fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) and a second fuel supply channel (20) may be coaxially arranged in a fuel delivery structure (12). A first set of vanes 22 includes a radial passage (24) in fluid communication with the first channel (18) to receive a first fuel. Passage (24) branches into passages (26) each having an aperture (28) to inject the first fuel without jet in cross-flow injection. A second set of vanes (32) includes a radial passage (34) in fluid communication with the second channel (20) to receive a second fuel. Passage (34) branches into passages (36) each having an aperture (38) arranged to inject the second fuel also without jet in cross-flow injection. This arrangement may be effective to reduce flashback that otherwise may be encountered in fuels having a relatively high flame speed.Type: ApplicationFiled: January 29, 2015Publication date: January 25, 2018Inventors: Walter Ray Laster, Jacob William Hardes, Robert H. Bartley, Mario Gaviria
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Publication number: 20170363291Abstract: A fuel injector for injecting alternate fuels having a different energy density in a gas turbine is provided. A first fuel supply channel (18) may be fluidly coupled to a radial passage (22) in a plurality of vanes (20) that branches into passages (24) (e.g., axial passages) to inject a first fuel without jet in cross-flow injection. This may be effective to reduce flashback in fuels having a relatively high flame speed. A mixer (30) with lobes (32) for injection of a second fuel may be arranged at the downstream end of a fuel delivery tube (12). A fuel-routing structure (38) may be configured to route the second fuel within a respective lobe so that fuel injection of the second fuel takes place radially outwardly relative to a central region of the mixer. This may be conducive to an improved (e.g., a relatively more uniform) mixing of air and fuel.Type: ApplicationFiled: January 29, 2015Publication date: December 21, 2017Inventors: Walter Ray Laster, Timothy A. Fox, Robert H. Bartley
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Publication number: 20170284210Abstract: A transition-to-turbine seal assembly is provided. Seal members (52, 58) may include one or more anchoring tabs (54, 60) affixed only to an associated transition (56) and not to a neighboring transition (57). Thus, seal members (52, 58) may be practically free from high stress levels due to differing motion that can arise between neighboring transitions (56, 57). Additionally, seal members (100, 120) may include articulating segments (106, 108, 126, 128) arranged to provide a respective degree of freedom along a desired direction so that the seal members may be practically free from high stress levels while providing an effective sealing functionality.Type: ApplicationFiled: September 5, 2014Publication date: October 5, 2017Inventors: Robert H. BARTLEY, Matthias HASE, Adam J. WEAVER, Lashanda N. WILLIAMS
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Publication number: 20170268355Abstract: A transition duct support apparatus and a method to support an exit frame in a transition duct in a gas turbine engine are provided. A stiffener (24) may be arranged to provide support to an outer edge (27) of an exit frame (12) in a transition duct (14). Stiffener (24) may be configured to circumferentially extend between mutually opposed corners (30) of the exit frame of the transition duct. A brace (26) may be connected to a centrally-disposed section (20) and may extend to support respective end portions (32) of the stiffener. The support apparatus is effective to provide a respective tuned level of stiffness support with respect to one or more axes of the exit frame in the transition duct. The apparatus and method may be effective for distributing mechanical stresses on the exit frame of the transition duct and/or neighboring regions in the transition duct.Type: ApplicationFiled: December 11, 2014Publication date: September 21, 2017Inventors: Manish Kumar, Joseph L. Evins, Khamhou Sayavong, Matthias Hase, Miguel Bascones, Adam J. Weaver, Robert H. Bartley, Lashanda N. Williams
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Publication number: 20170234542Abstract: A fuel burner system (10) configured to inject a liquid fuel and a gas fuel into a combustor (12) of a turbine engine (14) such that the engine (14) may operate on the combustion of both fuel sources (20, 24) is disclosed. The fuel burner system (10) may be formed from a nozzle cap (16) including one or more first fuel injection ports (18) in fluid communication with a first fuel source (20) of syngas and one or more second fuel injection ports (22) in fluid communication with a second fuel source (24) of natural gas. The fuel burner system (10) may also include an oil lance (26) with one or more oil injection passages (28) that is in fluid communication with at least one oil source (30) and is configured to emit oil into the combustor (12). The oil lance (26) may include one or more fluid injection passages (32) configured to emit air to break up the oil spray and water to cool the combustor (12), or both.Type: ApplicationFiled: October 23, 2014Publication date: August 17, 2017Applicant: Siemens AktiengesellschaftInventors: Vinayak V. Barve, Timothy A. Fox, Robert H. Bartley, Sachin Terdalkar
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Patent number: 9322558Abstract: A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.Type: GrantFiled: June 27, 2013Date of Patent: April 26, 2016Assignee: SIEMENS AKTIENGESELLSCHAFTInventors: Stephen A. Ramier, David J. Wiebe, Lawrence P. Budnick, Mark L. Adamson, Daniel W. Garan, Robert H. Bartley, Yadollah Naghian
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Patent number: 9267689Abstract: A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.Type: GrantFiled: March 4, 2013Date of Patent: February 23, 2016Assignee: Siemens AktiengesellschaftInventors: David J. Wiebe, Stephen A. Ramier, Robert H. Bartley, Daniel W. Garan, Erick J. Deane, Mark L. Adamson, Yadollah Naghian
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Publication number: 20150000283Abstract: A combustor apparatus defining a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus comprises an outer wall including a fuel inlet opening for receiving a fuel feed pipe. A coupling assembly is engaged with the fuel feed pipe at the fuel inlet opening to attach the fuel feed pipe to the outer wall. A fuel injection system is located in the interior volume of the outer wall and comprises fuel supply structure including a fuel feed block having a fuel intake passage aligned with the outlet portion of the fuel feed pipe. A coupling fastener is engaged against an exterior outer face of the fuel feed block to create a sealed coupling for containing fuel passing from the fuel feed pipe into the fuel feed block, and to secure the fuel feed block relative to the coupling assembly.Type: ApplicationFiled: June 27, 2013Publication date: January 1, 2015Inventors: Stephen A. Ramier, David J. Wiebe, Lawrence P. Budnick, Mark L. Adamson, Daniel W. Garan, Robert H. Bartley, Yadollah Naghian
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Publication number: 20140245740Abstract: A combustor apparatus defines a combustion zone where air and fuel are burned to create high temperature combustion products. The combustor apparatus includes an outer wall, coupling structure on the outer wall adjacent to a fuel inlet opening thereof, a fuel injection system, a fuel feed assembly, and a fitting member. The fuel injection system provides fuel to be burned in the combustion zone. The fuel supply structure includes a threaded inner surface formed from a first material. The fuel feed assembly includes a fuel feed pipe that extends through the fuel inlet opening in the outer wall and has an outlet portion formed from the first material and that is threadedly engaged with the fuel supply structure, and an inlet portion affixed to the outlet portion and formed from a second material. The fitting member secures the fuel feed assembly relative to the outer wall.Type: ApplicationFiled: March 4, 2013Publication date: September 4, 2014Inventors: David J. Wiebe, Stephen A. Ramier, Robert H. Bartley, Daniel W. Garan, Erick J. Deane, Mark L. Adamson, Yadollah Naghian