Patents by Inventor Ronald B. Pardington
Ronald B. Pardington 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: 9404422Abstract: In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow guide receives an air flow. The assembly further includes a swirler apparatus coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly.Type: GrantFiled: May 23, 2013Date of Patent: August 2, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Frank J. Zupanc, Ronald B. Pardington, Paul Yankowich
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Patent number: 9021812Abstract: A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.Type: GrantFiled: July 27, 2012Date of Patent: May 5, 2015Assignee: Honeywell International Inc.Inventors: Ronald B. Pardington, Paul Yankowich, Nagaraja S. Rudrapatna, Thomas Frank Johnson
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Publication number: 20140345286Abstract: In accordance with an exemplary embodiment, a fuel injector assembly is provided for a gas turbine engine with a compressor section and a combustion section. The fuel injector assembly includes a stem defining a fuel path for fuel and a flow guide coupled to and extending along the stem. The flow guide receives an air flow. The assembly further includes a swirler apparatus coupled to the stem and configured to receive the fuel. The swirler apparatus is further coupled to the flow guide and configured to receive the air flow. The swirler apparatus is configured to mix the fuel and the air flow and direct the mixture into a combustor of the combustor assembly.Type: ApplicationFiled: May 23, 2013Publication date: November 27, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Frank J. Zupanc, Ronald B. Pardington, Paul Yankowich
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Publication number: 20140026580Abstract: A combustor dome and heat-shield assembly comprises a heat-shield having a first opening therethrough. A swirler extends through the first opening and captures the heat-shield. A dome having a second opening therethrough and has an upstream side and a downstream side. The swirler extends through the second opening from the downstream side to the upstream side to capture the heat-shield on the downstream side, and a retaining clip engages the swirler to secure the swirler and the heat-shield on the dome.Type: ApplicationFiled: July 27, 2012Publication date: January 30, 2014Applicant: Honeywell International Inc.Inventors: Ronald B. Pardington, Paul Yankowich, Nagaraja S. Rudrapatna, Thomas Frank Johnson
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Patent number: 7905094Abstract: A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction. The first group of cooling holes include a generally circumferential first row of cooling holes, a generally circumferential second row of cooling holes immediately downstream from, consecutive to, and separated from the first row at a first distance, a generally circumferential third row of cooling holes immediately downstream from, consecutive to, and separated from the second row at a second distance, and a generally circumferential fourth row of cooling holes immediately downstream from, consecutive to, and separated from the third row at a third distance. The first distance is greater than the second distance and the third distance, and the second distance is greater than the third distance.Type: GrantFiled: September 28, 2007Date of Patent: March 15, 2011Assignee: Honeywell International Inc.Inventors: Rodolphe Dudebout, Paul R. Yankowich, Frank J. Zupanc, Ronald B. Pardington
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Publication number: 20090293486Abstract: A combustor for a gas turbine engine is provided, and includes an inner case; an outer case circumscribing the inner case and forming an annular pressure vessel therebetween; an inner liner positioned within the annular pressure vessel; an outer liner circumscribing the inner liner and forming a combustion chamber with the inner liner; and an igniter coupled to the outer case and extending to the outer liner such that the igniter is positioned to ignite an air and fuel mixture in the combustion chamber. The igniter includes a protrusion for coupling the igniter to the outer liner.Type: ApplicationFiled: October 26, 2007Publication date: December 3, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Amy T. Hanson, Ronald B. Pardington
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Patent number: 7617689Abstract: A retaining ring is provided for use in conjunction with a carburetor assembly having a flow passage therethrough for conducting a fuel-air mixture into a combustion chamber, the carburetor assembly comprising an air flow modifier and a fuel injector receiving element adjacent thereto. The retaining ring comprises a collar configured to engage the fuel injector receiving element so as to maintain its position adjacent the air flow modifier, and a retaining portion coupled to the collar and configured to engage the air flow modifier to secure the airflow modifier to the combustion chamber. The retaining portion cooperates with the collar to form an aperture through the retaining ring for receiving the carburetor assembly.Type: GrantFiled: March 2, 2006Date of Patent: November 17, 2009Assignee: Honeywell International Inc.Inventors: Jurgen C. Schumacher, Frank J. Zupanc, Paul R. Yankowich, Ronald B. Pardington
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Publication number: 20090090110Abstract: A dome assembly for a gas turbine engine includes a plurality of faceted segments and a plurality of openings. The plurality of faceted segments are coupled together to form a dome structure that is configured to be disposed between an inner liner and an outer liner that circumscribes the inner liner. The plurality of openings are each opening formed within a respective faceted segment, and are configured to at least partially house an atomizer therein. Each faceted segment is at least substantially flat.Type: ApplicationFiled: October 4, 2007Publication date: April 9, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Ronald B. Pardington, Jonathan N. Kettinger
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Publication number: 20090084110Abstract: A combustor liner assembly includes a liner and a first group of cooling holes formed in the liner and having an increasing density in a downstream direction.Type: ApplicationFiled: September 28, 2007Publication date: April 2, 2009Applicant: HONEYWELL INTERNATIONAL, INC.Inventors: Rodolphe Dudebout, Paul R. Yankowich, Frank J. Zupanc, Ronald B. Pardington
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Patent number: 6101806Abstract: A turbine engine is disclosed that is capable of operating in an emergency power mode, an air breathing auxiliary power mode and a bypass bleed environmental control mode. In a preferred embodiment of the invention, the engine comprises in working fluid flow order a compressor for compressing air, a combustion chamber and a power turbine for extracting mechanical work from heated and/or compressed air. The compressor and turbine are separately coupled by a shaft which is also coupled to a generator for supplying electrical power and a cooling turbine for supplying cooled air to the aircraft cabin and avionics. The combustion chamber has an upstream combustor inlet and a downstream combustor inlet, each of which may admit compressed air either to be mixed with fuel for combustion, or to pass directly to the combustor outlet which is operatively attached to the power turbine section inlet.Type: GrantFiled: August 31, 1998Date of Patent: August 15, 2000Assignee: AlliedSignal, Inc.Inventors: Daih-Yeou Chen, Cristopher Frost, Hans Heydrich, Ronald B. Pardington