Patents by Inventor William Proscia
William Proscia 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: 20240102655Abstract: A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.Type: ApplicationFiled: February 3, 2023Publication date: March 28, 2024Applicant: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Justin M Locke, Dennis M Moura, Duane C McCormick, Scott A Liljenberg, Theodore R Strickland, William Proscia
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Patent number: 11598527Abstract: A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.Type: GrantFiled: June 9, 2016Date of Patent: March 7, 2023Assignee: Raytheon Technologies CorporationInventors: Justin M. Locke, Dennis Moura, Duane McCormick, Scott A. Liljenberg, Theodore Strickland, William Proscia
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Patent number: 11378275Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.Type: GrantFiled: December 6, 2019Date of Patent: July 5, 2022Assignee: Raytheon Technologies CorporationInventors: Justin M. Locke, Timothy S. Snyder, William Proscia
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Patent number: 11365884Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.Type: GrantFiled: March 18, 2020Date of Patent: June 21, 2022Assignee: Raytheon Technologies CorporationInventor: William Proscia
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Patent number: 11230940Abstract: A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.Type: GrantFiled: August 31, 2020Date of Patent: January 25, 2022Assignee: Raytheon Technologies CorporationInventors: Michael G. McCaffrey, Joseph D. Evetts, Kristine M. Carnavos, Conway Chuong, Christopher W. Robak, William Proscia, Purity Dele-Oni, Caroline Karanian, John E. Paul, Jagannath Pranatharthikaran
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Publication number: 20210172604Abstract: An assembly is provided for a turbine engine. This assembly includes a swirler and a fuel nozzle. The swirler is configured with an outer wall, an inner wall, an outer passage and an inner passage. The outer wall circumscribes the inner wall and extends axially along an axis to a distal outer wall end. The inner wall extends axially along the axis to a distal inner wall end that is axially recessed within the swirler from the distal outer wall end. The outer passage is formed by and radially between the inner wall and the outer wall. The inner passage is formed by and radially within the inner wall. The fuel nozzle projects into the inner passage. The fuel nozzle is configured with a plurality of orifices axially aligned with the inner wall and arranged circumferentially about the axis.Type: ApplicationFiled: December 6, 2019Publication date: June 10, 2021Inventors: Justin M. Locke, Timothy S. Snyder, William Proscia
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Patent number: 10738704Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.Type: GrantFiled: October 3, 2016Date of Patent: August 11, 2020Assignee: Raytheon Technologies CorporationInventor: William Proscia
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Patent number: 10739003Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.Type: GrantFiled: October 3, 2016Date of Patent: August 11, 2020Assignee: United Technologies CorporationInventor: William Proscia
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Publication number: 20200217508Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.Type: ApplicationFiled: March 18, 2020Publication date: July 9, 2020Applicant: United Technologies CorporationInventor: William Proscia
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Patent number: 10508811Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased circumferential fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased circumferential fuel distribution within a swirler of a radial fuel injection system.Type: GrantFiled: October 3, 2016Date of Patent: December 17, 2019Assignee: United Technologies CorporationInventor: William Proscia
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Patent number: 10393030Abstract: Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at least one injection aperture a first injection depth from the exit of the swirler and a second subcircuit having at least one second injection aperture located at a second injection depth from the exit of the swirler, wherein the first injection depth is greater than the second injection depth.Type: GrantFiled: October 3, 2016Date of Patent: August 27, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: William Proscia
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Publication number: 20180163629Abstract: A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply a first percentage of fuel and a radial fuel injection system that communicates with the combustion chamber downstream of the axial fuel injection system, the radial fuel injection system operable to supply a second percentage of fuel, the first percentage and the second percentage of fuel scheduled in response to an engine operating parameter.Type: ApplicationFiled: October 3, 2016Publication date: June 14, 2018Applicant: United Technologies CorporationInventor: William Proscia
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Publication number: 20180094590Abstract: Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at least one injection aperture a first injection depth from the exit of the swirler and a second subcircuit having at least one second injection aperture located at a second injection depth from the exit of the swirler, wherein the first injection depth is greater than the second injection depth.Type: ApplicationFiled: October 3, 2016Publication date: April 5, 2018Inventor: William Proscia
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Publication number: 20180094817Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased circumferential fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased circumferential fuel distribution within a swirler of a radial fuel injection system.Type: ApplicationFiled: October 3, 2016Publication date: April 5, 2018Applicant: United Technologies CorporationInventor: William Proscia
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Publication number: 20180094814Abstract: An injector of a radial fuel injection system for a combustor of a gas turbine engine includes a swirler; and a fuel nozzle located within the swirler, the fuel nozzle located within the swirler, the fuel nozzle operable to provide a biased radial fuel distribution within the swirler. A method of controlling a fuel flow to a combustor of a gas turbine engine includes selectively controlling a biased radial fuel distribution within a swirler of a radial fuel injection system.Type: ApplicationFiled: October 3, 2016Publication date: April 5, 2018Applicant: United Technologies CorporationInventor: William Proscia
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Publication number: 20170356654Abstract: A method of reducing noise from a combustor of a gas turbine engine includes the steps of establishing a maximum noise limit that may be for a particular frequency range. A primary fuel flow percentage, which may be emitted from a fuel nozzle arrangement having various groupings of simplex and duplex nozzles, is then established. An immersion depth measured between an aft rim of a swirler and a distal tip of the fuel nozzles may then be reduced thereby reducing the noise amplitude.Type: ApplicationFiled: June 9, 2016Publication date: December 14, 2017Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Justin M. Locke, Dennis Moura, Duane McCormick, Scott A. Liljenberg, Theodore Strickland, William Proscia
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Patent number: 9631560Abstract: A method of noise control from a combustor of a gas turbine engine includes selectively forming a plurality of local circumferential zones with different fuel-air ratios within the combustor.Type: GrantFiled: November 22, 2011Date of Patent: April 25, 2017Assignee: United Technologies CorporationInventors: James B. Hoke, William Proscia
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Patent number: 9127837Abstract: An improved induced draft gas burner assembly for low NOx residential and light commercial gas furnaces is disclosed. The improved burner includes an upstream assembly coupled to a fuel inlet and an air inlet. The air inlet is coupled to a neck extending between the air inlet and the outlet of the neck, both of which may be disposed within an optional chamber. If used, such a chamber also includes an outlet coupled to a burner. In practice, the chamber and neck behave as a Helmholtz resonator that can be tuned to provide an upstream impedance Zup that exceeds the downstream impedance Zdown of the components downstream of the burner assembly.Type: GrantFiled: June 22, 2011Date of Patent: September 8, 2015Assignee: Carrier CorporationInventors: William Proscia, Scott A. Liljenberg, William J. Roy, Duane C. McCormick, Christopher T. Chipman
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Publication number: 20130125556Abstract: A method of noise control from a combustor of a gas turbine engine includes selectively forming a plurality of local circumferential zones with different fuel-air ratios within the combustor.Type: ApplicationFiled: November 22, 2011Publication date: May 23, 2013Inventors: James B. Hoke, William Proscia
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Publication number: 20110311924Abstract: An improved induced draft gas burner assembly (31, 131, 231, 331, 431, 531, 631) for low NOx residential and light commercial gas furnaces (10, 10a) is disclosed. The improved burner includes an upstream assembly coupled to a fuel inlet (55) and an air inlet (43). The air inlet (43) is coupled to a neck (41, 141, 241, 341, 441, 541, 641) extending between the air inlet (43) and the outlet of the neck (41, 141, 241, 341, 441, 541, 641), both of which may be disposed within an optional chamber (42, 142, 242, 342, 442). If used, such a chamber (42, 142, 242, 342, 442) also includes an outlet coupled to a burner (46, 146, 246, 346, 546, 646). In practice, the chamber (42, 142, 242, 342, 442) and neck (41, 141, 241, 341, 441, 541, 641) behave as a Helmholtz resonator that can be tuned to provide an upstream impedance Zup that exceeds the downstream impedance Zdown of the components downstream of the burner assembly (31, 131, 231, 331, 431, 531, 631).Type: ApplicationFiled: June 22, 2011Publication date: December 22, 2011Applicant: Carrier CorporationInventors: William Proscia, Scott A. Liljenberg, William J. Roy, Duane C. McCormick, Christopher T. Chipman