Patents by Inventor John Henriquez
John Henriquez 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: 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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Patent number: 9121279Abstract: A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.Type: GrantFiled: October 8, 2010Date of Patent: September 1, 2015Assignee: Alstom Technology LtdInventors: Sherman Craig Creighton, Charles Ellis, David John Henriquez, Peter Stuttaford
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Publication number: 20150226127Abstract: Aspects of the present invention relate to systems and method for fabricating a combustor end cover where the cover does not include braze joints within the cover. The combustor cover provides a configuration and method of manufacturing where all fuel and air annuli can be placed within the cover without requiring use of brazed inserts, which were previously known to crack and leak.Type: ApplicationFiled: February 13, 2015Publication date: August 13, 2015Inventors: KEVIN BRADY POWELL, David John Henriquez, Paul Economo
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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: 8322146Abstract: 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: GrantFiled: August 22, 2008Date of Patent: December 4, 2012Assignee: Alstom Technology LtdInventors: Hany Rizkalla, Stephen W. Jorgensen, Peter Stuttaford, Plazi Ricklin, David John Henriquez
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Publication number: 20120085099Abstract: A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.Type: ApplicationFiled: October 8, 2010Publication date: April 12, 2012Applicant: ALSTOM TECHNOLOGY LTDInventors: Sherman Craig Creighton, Charles Ellis, David John Henriquez, 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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Patent number: 7299620Abstract: An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.Type: GrantFiled: June 29, 2004Date of Patent: November 27, 2007Inventors: Peter Stuttaford, John Henriquez, Paul Economo
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Patent number: 7287382Abstract: An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into the end cover. The fluids within the end cover are kept separate proximate each of the plurality of first openings by a wall that is integrally formed from a portion of the end cover plate.Type: GrantFiled: July 19, 2004Date of Patent: October 30, 2007Inventor: John Henriquez
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Patent number: 7000403Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.Type: GrantFiled: March 12, 2004Date of Patent: February 21, 2006Assignee: Power Systems Mfg., LLCInventors: John Henriquez, Jacob McLeroy, Brian R. Mack, Vincent C. Martling
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Publication number: 20060010873Abstract: An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifolds machined into the end cover. The fluids within the end cover are kept separate proximate each of the plurality of first openings by a wall that is integrally formed from a portion of the end cover plate.Type: ApplicationFiled: July 19, 2004Publication date: January 19, 2006Applicant: POWER SYSTEMS MFG., LLCInventor: John Henriquez
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Publication number: 20050284442Abstract: An ignition system having improved reliability for a gas turbine combustor is disclosed. The ignition system comprises an outer housing having at least one fuel passage and an electrode extending therethrough forming a generally annular passage for cooling air to pass to a mixing chamber. Fuel and air mix in the mixing chamber to form a combustible mixture that is ignited by the electrode. The outer housing further comprises a plurality of air swirl holes to effectively cool the walls of the mixing chamber as well as to provide improved flame stability.Type: ApplicationFiled: June 29, 2004Publication date: December 29, 2005Inventors: Peter Stuttaford, John Henriquez, Paul Economo
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Publication number: 20050274827Abstract: The present invention discloses a means for restricting a flow of fuel to a fuel nozzle assembly for a gas turbine combustor such that the fuel nozzle assembly can be manufactured to accommodate a variety of engine configurations and flow conditions. Multiple embodiments of the present invention are disclosed with each embodiment generally directed towards a nozzle located generally along the centerline of a two-stage combustor.Type: ApplicationFiled: June 14, 2004Publication date: December 15, 2005Inventor: John Henriquez
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Publication number: 20050198965Abstract: A fuel nozzle and gas turbine combustor capable of operating on multiple fuels with reduced carbon build-up to the fuel nozzle and adjacent combustor components is disclosed. The fuel nozzle incorporates a reconfigured gas fuel assembly and mixing tube to eliminate known areas of recirculation. Furthermore, the liquid fuel assembly includes reconfigured spray characteristics to further reduce droplet interaction with the mixing tube.Type: ApplicationFiled: March 12, 2004Publication date: September 15, 2005Inventors: John Henriquez, Jacob McLeroy, Brian Mack, Vincent Martling