Patents by Inventor Terrel Kuhn
Terrel Kuhn 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: 9400110Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.Type: GrantFiled: October 19, 2012Date of Patent: July 26, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
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Patent number: 9080770Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: GrantFiled: June 6, 2011Date of Patent: July 14, 2015Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghave Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
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Publication number: 20140109581Abstract: A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner.Type: ApplicationFiled: October 19, 2012Publication date: April 24, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Terrel Kuhn, Vinayender Kuchana, Veeraraghava Raju Hasti, Raymond Gage, Sunil James
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Patent number: 8534076Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.Type: GrantFiled: June 9, 2009Date of Patent: September 17, 2013Assignee: Honeywell Internationl Inc.Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn
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Publication number: 20120304647Abstract: A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner.Type: ApplicationFiled: June 6, 2011Publication date: December 6, 2012Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Rodolphe Dudebout, Veeraraghava Raju Hasti, Terrel Kuhn, Sunil James, Mario Scaini
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Publication number: 20100307166Abstract: A combustor-turbine seal interface is provided for deployment within a gas turbine engine. In one embodiment, the combustor-turbine assembly a combustor, a turbine nozzle downstream of the combustor, and a first compliant dual seal assembly. The first compliant dual seal assembly includes a compliant seal wall sealingly coupled between the combustor and the turbine nozzle, a first compression seal sealingly disposed between the compliant seal wall and the turbine nozzle, and a first bearing seal generally defined by the compliant seal wall and the turbine nozzle. The first bearing seal is sealingly disposed in series with the first compression seal.Type: ApplicationFiled: June 9, 2009Publication date: December 9, 2010Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Gregory O. Woodcock, Bradley Reed Tucker, Jason Smoke, Stony Kujala, Terrel Kuhn
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Publication number: 20060207095Abstract: A method for controlling combustor liner carbon formation on repaired combustors includes making modular effusion panel subassemblies remote from the combustor liner; removing a non-effusion or damaged panel from the combustor liner; and replacing the non-effusion or damaged panel with the modular effusion panel.Type: ApplicationFiled: February 5, 2004Publication date: September 21, 2006Applicant: Honeywell International Inc.Inventors: Terrel Kuhn, William Freeman, Francis Maszk, Douglas Freiberg, Kenneth Struzek, Lawrence Kobold
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Publication number: 20050247065Abstract: A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate in communication with the premix chamber wall at the chamber inlet end, the chamber inlet plate having a fuel nozzle inlet hole disposed through the chamber inlet plate, the chamber inlet plate further comprising a plurality of swirler passages disposed through the chamber inlet plate, and the chamber outlet end being open. A method of producing turbine gas is also disclosed.Type: ApplicationFiled: May 4, 2004Publication date: November 10, 2005Applicant: Honeywell International Inc.Inventors: Rodolphe Dudebout, Terrel Kuhn, Paul Yankowich, Frank Zupanc