Patents by Inventor Hany Rizkalla
Hany Rizkalla 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: 20090188255Abstract: A combustor end cap assembly having an improved cooling configuration is disclosed. Embodiments of the present invention are directed towards an apparatus and method for cooling an effusion plate of the combustor end cap assembly. The combustor end cap assembly also incorporates an impingement plate having a plurality of cooling holes with the impingement plate positioned a predetermined distance from the effusion plate. The cooling fluid passes through the impingement plate and is directed towards and onto the effusion plate for cooling of the effusion plate.Type: ApplicationFiled: October 8, 2008Publication date: July 30, 2009Applicant: Alstom Technologies Ltd. LLCInventors: Andrew Green, Peter Stuttaford, Yan Chen, Hany Rizkalla
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Publication number: 20090188258Abstract: A transition duct having a thermally free aft frame and being capable of adjusting the natural frequency is disclosed. The aft frame is capable of permitting movement due to thermal gradients with the transition duct. The transition duct utilizes a spring plate located adjacent to an aft mounting bracket, where the spring plate, based on its thickness can either increase or decrease a frequency of the transition duct. Such an arrangement ensures that the transition duct natural frequency does not coincide with or cross other critical engine and/or combustor frequencies.Type: ApplicationFiled: September 29, 2008Publication date: July 30, 2009Applicant: ALSTOM TECHNOLOGIES LTD. LLCInventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford
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Publication number: 20090145137Abstract: A transition duct assembly with a thermally free aft frame and mounting system for use in a gas turbine engine are disclosed. The aft frame is capable of adjusting to thermal gradients while the mounting system provides for at least transverse movement of the transition duct during engine assembly. The mounting system also provides a means for raising the natural frequency of the transition duct outside of the engine's dynamic excitation ranges.Type: ApplicationFiled: August 22, 2008Publication date: June 11, 2009Applicant: ALSTOM TECHNOLOGIES, LTD., LLCInventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford, Plazi Ricklin, David John Henriquez
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Publication number: 20090145983Abstract: Embodiments for minimizing relative thermal growth within a fuel nozzle of a gas turbine combustor are disclosed. Fuel nozzle configurations are provided in which a heating fluid is provided to one or more passages in a fuel nozzle from feed holes in the fuel nozzle base. The heating fluid passes through the fuel nozzle, thereby raising the operating temperature of portions of the fuel nozzle to reduce differences in thermal gradients within the fuel nozzle. Various fuel nozzle configurations and passageway geometries are also disclosed.Type: ApplicationFiled: December 10, 2007Publication date: June 11, 2009Applicant: POWER SYSTEMS MFG., LLCInventors: Peter Stuttaford, Paul Economo, Khalid Oumejjoud, Max Dufflocq, Hany Rizkalla
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Patent number: 7007482Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.Type: GrantFiled: May 28, 2004Date of Patent: March 7, 2006Assignee: Power Systems Mfg., LLCInventors: Andrew Green, Peter Stuttaford, Jeffrey Arthur Benoit, Vamsi Duraibabu, Hany Rizkalla
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Publication number: 20050262844Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness and heat transfer along the aft end of the combustion liner is improved, resulting in extended component life. The region of the combustion liner proximate its second end comprises a plurality of first feed holes, a plurality of spring seals that seal against a transition duct, a cooling ring having a plurality of second feed holes, that with the first feed holes pass a cooling fluid into an annulus formed between the cooling ring and combustion liner. The cooling fluid passes over a means for augmenting the heat transfer proximate the combustion liner second end, wherein the heat transfer augmentation preferably comprises a plurality of raised ridges that increases the surface area of the outer liner wall to turbulate the cooling fluid and maximize the cooling effectiveness.Type: ApplicationFiled: May 28, 2004Publication date: December 1, 2005Inventors: Andrew Green, Peter Stuttaford, Jeffrey Benoit, Vamsi Duraibabu, Hany Rizkalla
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Patent number: 6935116Abstract: A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, and precise three dimensional staging between fuel injectors. Axial, radial, and circumferential fuel staging is utilized including fuel injection proximate air swirlers. Furthermore, strong recirculation zones are established proximate the introduction of fuel and air premixture from different stages to the combustion zone. The combination of the strong recirculation zones, efficient premixing, and staged fuel flow thereby provide the opportunity to produce low emissions combustion at various load conditions.Type: GrantFiled: April 28, 2003Date of Patent: August 30, 2005Assignee: Power Systems Mfg., LLCInventors: Peter J. Stuttaford, Stephen Jennings, Andrew Green, Ryan McMahon, Yan Chen, Hany Rizkalla, John Carella, Vamsi Duraibabu, Martin Spalding
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Patent number: 6915636Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.Type: GrantFiled: June 19, 2003Date of Patent: July 12, 2005Assignee: Power Systems Mfg., LLCInventors: Peter Stuttaford, Stephen T. Jennings, Ryan McMahon, Hany Rizkalla, Alfredo Cires
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Patent number: 6898937Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.Type: GrantFiled: June 2, 2003Date of Patent: May 31, 2005Assignee: Power Systems Mfg., LLCInventors: Peter Stuttaford, Stephen T. Jennings, Ryan McMahon, Hany Rizkalla, Alfredo Cires
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Patent number: 6886346Abstract: A pilot fuel nozzle configuration for use in a combustor is disclosed having a natural frequency outside the range of the operating frequencies of a gas turbine engine. Multiple embodiments are disclosed for the improved pilot fuel nozzle including configurations for newly manufactured nozzles, repair to existing pilot nozzles, as well as multiple natural frequency levels for the improved pilot fuel nozzle. The pilot fuel nozzle comprises an elongated housing, first and second flanges, and a nozzle tip, with the first flange fixed to the elongated housing at a first end and the nozzle tip fixed to the second end, opposite of the first end. The second flange is fixed along the elongated housing and is used for attaching the pilot fuel nozzle to a combustor. The present invention incorporates an increased wall thickness along at least a mid-span portion of the pilot nozzle to increase the stiffness and change the natural frequency.Type: GrantFiled: August 20, 2003Date of Patent: May 3, 2005Assignee: Power Systems Mfg., LLCInventors: Peter A. Sobieski, Kelly Shawn Smith, Alan Lovelace, Hany Rizkalla
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Publication number: 20050039460Abstract: A pilot fuel nozzle configuration for use in a combustor is disclosed having a natural frequency outside the range of the operating frequencies of a gas turbine engine. Multiple embodiments are disclosed for the improved pilot fuel nozzle including configurations for newly manufactured nozzles, repair to existing pilot nozzles, as well as multiple natural frequency levels for the improved pilot fuel nozzle. The pilot fuel nozzle comprises an elongated housing, first and second flanges, and a nozzle tip, with the first flange fixed to the elongated housing at a first end and the nozzle tip fixed to the second end, opposite of the first end. The second flange is fixed along the elongated housing and is used for attaching the pilot fuel nozzle to a combustor. The present invention incorporates an increased wall thickness along at least a mid-span portion of the pilot nozzle to increase the stiffness and change the natural frequency.Type: ApplicationFiled: August 20, 2003Publication date: February 24, 2005Inventors: Peter Sobieski, Kelly Smith, Alan Lovelace, Hany Rizkalla
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Publication number: 20040211186Abstract: A gas turbine combustion system having reduced emissions and improved flame stability at multiple load conditions is disclosed. The improved combustion system accomplishes this through complete premixing, a plurality of fuel injector locations, combustor geometry, and precise three dimensional staging between fuel injectors. Axial, radial, and circumferential fuel staging is utilized including fuel injection proximate air swirlers. Furthermore, strong recirculation zones are established proximate the introduction of fuel and air premixture from different stages to the combustion zone. The combination of the strong recirculation zones, efficient premixing, and staged fuel flow thereby provide the opportunity to produce low emissions combustion at various load conditions.Type: ApplicationFiled: April 28, 2003Publication date: October 28, 2004Inventors: Peter J. Stuttaford, Stephen Jennings, Andrew Green, Ryan McMahon, Yan Chen, Hany Rizkalla, John Carella, Vamsi Duraibabu, Martin Spalding
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Publication number: 20040006992Abstract: A premix fuel nozzle and method of operation for use in a gas turbine combustor is disclosed. The premix fuel nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of fuel and compressed air in order to provide a more uniform injection pattern. The fuel and compressed air mixes upstream of the combustion chamber and flows into the combustion chamber as a homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide fuel and compressed air to the fin assembly, as well as compressed air to cool the nozzle cap assembly. An alternate embodiment includes an additional fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly. A second alternate embodiment is disclosed which reconfigures the injector assembly and fuel injection locations to minimize flow blockage issues at the injector assembly.Type: ApplicationFiled: June 2, 2003Publication date: January 15, 2004Inventors: Peter Stuttaford, Stephen T. Jennings, Ryan McMahon, Hany Rizkalla, Alfredo Cires
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Publication number: 20040006993Abstract: A dual fuel premix nozzle and method of operation for use in a gas turbine combustor is disclosed. The dual fuel premix nozzle utilizes a fin assembly comprising a plurality of radially extending fins for injection of gas fuel and compressed air in order to provide a more uniform injection pattern and homogeneous mixture. The premix fuel nozzle includes a plurality of coaxial passages, which provide gaseous fuel and compressed air to the fin assembly. When in liquid fuel operation, the gas circuits are purged with compressed air and liquid fuel and water pass through coaxial passages to the tip of the dual fuel premix fuel nozzle, where they inject liquid fuel and water into the secondary combustion chamber. An alternate embodiment includes an additional gas fuel injection region located along a conically tapered portion of the premixed fuel nozzle, downstream of the fin assembly.Type: ApplicationFiled: June 19, 2003Publication date: January 15, 2004Inventors: Peter Stuttaford, Stephen T. Jennings, Ryan McMahon, Hany Rizkalla, Alfredo Cires