Patents by Inventor Alfredo Cires
Alfredo Cires 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: 10739007Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.Type: GrantFiled: May 9, 2018Date of Patent: August 11, 2020Assignee: POWER SYSTEMS MFG., LLCInventors: Alfredo Cires, Peter Stuttaford, Matthew Yaquinto, Hany Rizkalla, Khalid Oumejjoud, Fred Hernandez, Bryan Kalb, Nicolas Demougeot, Joshua R McNally, Ramesh Keshava Bhattu, Bernard Tam-Yen Sam
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Publication number: 20190346142Abstract: A diffusion cartridge assembly for a gas turbine engine, and methods of using the same. The diffusion cartridge assembly includes a tip plate with an array of fuel supply openings and a mounting hole radially inward of the array of fuel supply openings, an end cover, and an outer sleeve extending from the tip plate to the end cover and defining an open inner chamber. A fuel supply line is coupled to the end cover and extends within the open inner chamber toward the tip plate. A manifold is coupled to an end of the fuel supply line proximate to the tip plate, and includes an array of fuel injector tips. Each of the fuel injector tips extends through a respective one of the array of fuel supply openings in the tip plate. The manifold also includes a thermally free mounting pin extending into the mounting hole.Type: ApplicationFiled: May 9, 2018Publication date: November 14, 2019Inventors: Alfredo Cires, Peter Stuttaford, Matthew Yaquinto, Hany Rizkalla, Khalid Oumejjoud, Fred Hernandez, Bryan Kalb, Nicolas Demougeot, Joshua R. McNally, Ramesh Keshava Bhattu, Bernard Tam-Yen Sam
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Patent number: 9249978Abstract: A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.Type: GrantFiled: July 3, 2012Date of Patent: February 2, 2016Assignee: Alstom Technology LtdInventors: Brian K. Richardson, Alfredo Cires, John Henriquez, Daniel J. Sullivan, Kevin B. Powell
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Publication number: 20140007580Abstract: A gas turbine combustion liner having a novel and improved system for receiving a peripheral device through a floating collar is disclosed. The retaining collar assembly provides planar movement for receiving the peripheral device while preventing the floating collar from rotational movement through an anti-rotation tab on the collar and a collar cap, resulting in reduced wear to the peripheral device. The collar cap can include different configurations for reducing any vibratory effects caused by an oncoming airflow directly contacting the floating collar.Type: ApplicationFiled: July 3, 2012Publication date: January 9, 2014Applicant: ALSTOM TECHNOLOGY LTDInventors: BRIAN K. RICHARDSON, ALFREDO CIRES, JOHN HENRIQUEZ, DANIEL J. SULLIVAN, KEVIN B. POWELL
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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: 6857271Abstract: An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodiments of premix pilot nozzles are disclosed that have a fuel flow rate that can be controlled and adjusted as required, including a plate and feed hole combination, a pressfit premix pilot nozzle, and a premix pilot nozzle that is threaded into the secondary fuel nozzle assembly.Type: GrantFiled: December 16, 2002Date of Patent: February 22, 2005Assignee: Power Systems Mfg., LLCInventors: Robert J. Kraft, Alfredo Cires
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Publication number: 20040123597Abstract: An improved secondary fuel distribution system having a readily adjustable premix pilot nozzle for use in a gas turbine combustor is disclosed. The secondary fuel nozzle assembly has a premix fuel nozzle comprising an annular tubular manifold and a premix pilot nozzle. Multiple embodiments of premix pilot nozzles are disclosed that have a fuel flow rate that can be controlled and adjusted as required, including a plate and feed hole combination, a pressfit premix pilot nozzle, and a premix pilot nozzle that is threaded into the secondary fuel nozzle assembly.Type: ApplicationFiled: December 16, 2002Publication date: July 1, 2004Inventors: Robert J. Kraft, 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
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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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Patent number: 5813611Abstract: The C/D axisymmetrical exhaust nozzle for a gas turbine engine is designed to fit on the engine and STOVL aircraft and includes a combined load balancing piston/synchronization ring that is discretely attached to a fulcrum link for positioning the convergent and divergent flaps of the nozzle. The balancing piston which is motivated by engine's fan discharge air permits the use of smaller hydraulic actuators and the quantity of fuel used as the hydraulic medium required to meet the power needs is significantly reduced.Type: GrantFiled: September 27, 1996Date of Patent: September 29, 1998Assignee: United Technologies CorporationInventors: Alfredo Cires, Jennifer Groceman
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Patent number: 5782294Abstract: A liner apparatus is provided which includes an inner wall, a plurality of fasteners extending out from the inner wall, an impingement sheet attached to the inner wall by the fasteners, apparatus for spacing the inner wall and the impingement sheet a distance apart, and apparatus for sealing between the inner wall and the impingement sheet along an edge of the liner.Type: GrantFiled: December 18, 1995Date of Patent: July 21, 1998Assignee: United Technologies CorporationInventors: Kenneth W. Froemming, James W. Vehr, Caesar G. Mamplata, Alfredo Cires
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Patent number: 5080284Abstract: Disclosed is a device for cooling the trailing edge segment of a liner on a convergent flap of a nozzle on a gas turbine engine. The trailing edge cooling device enhances the cooling of the liner without introducing turbulence into the coolant, thereby allowing the coolant to be used to film cool downstream components. In addition, the present invention increases the longitudinal rigidity of the trailing edge of the liner to provide support for the trailing edge without significantly reducing the lateral flexibility of the liner required for thermal expansion.Type: GrantFiled: June 25, 1990Date of Patent: January 14, 1992Assignee: United Technologies CorporationInventor: Alfredo Cires
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Patent number: 5079912Abstract: Disclosed is an apparatus and a method for cooling a rotatable convergent side disk in a two-dimensional nozzle for a gas turbine engine, in which coolant is supplied and exhausted through concentric conduits, the cooling requirements of a liner assembly are reduced by use of a thermal barrier coating, and exhaust gas from the nozzle is prevented from aspirating into the side disk by use of a liner which is impervious to the exhaust gas.Type: GrantFiled: June 12, 1990Date of Patent: January 14, 1992Assignee: United Technologies CorporationInventors: Alfredo Cires, Richard D. Dickinson
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Patent number: 4747542Abstract: A cooling arrangement for the trailing edge of a nozzle flap 18 has a trailing edge liner 30,54 and a baffle plate 32,55. Air from plenum 22 passes through openings 38,54 to cool the trailing edge liner. Expansion of the nozzle liner 18 causes abutment seal 52 to open, increasing cooling air in proportion to the temperature of the nozzle liner.Type: GrantFiled: April 14, 1987Date of Patent: May 31, 1988Assignee: United Technologies CorporationInventors: Alfredo Cires, George D. Lee