Patents by Inventor Curtis C. Cowan
Curtis C. Cowan 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: 11519368Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.Type: GrantFiled: January 7, 2020Date of Patent: December 6, 2022Assignee: Raytheon Technologies CorporationInventors: Curtis C. Cowan, Rebecca R. Dunnigan, Gary D. Roberge
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Publication number: 20210207564Abstract: A cooling system for a gas turbine engine may comprise a plenum extending circumferentially around an outer engine case structure. The plenum may comprise a supply conduit and a return conduit. The supply conduit and the return conduit may be in fluid communication with a heat exchanger. The heat exchanger may be disposed between the outer engine case structure and an inner engine case structure. The plenum may be configured to provide enhance heat transfer for the cooling system.Type: ApplicationFiled: January 7, 2020Publication date: July 8, 2021Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Curtis C. Cowan, Rebecca R. Dunnigan, Gary D. Roberge
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Publication number: 20200240280Abstract: A slider seal assembly for a gas turbine engine, comprising a housing comprising an outer surface and an inner surface, and a recessed opening between the inner surface and the outer surface, wherein the inner surface of the housing includes a flat portion configured to match a receiver on an inner wall of a casing of the gas turbine engine; a seal plate received within the recessed opening and moveable relative to the housing; and a retaining ring configured to retain the seal plate adjacent the housing, the retaining ring includes a plurality of tabs configured to retain the seal plate adjacent the housing.Type: ApplicationFiled: January 29, 2019Publication date: July 30, 2020Applicant: United Technologies CorporationInventors: Curtis C. Cowan, Paul W. Duesler, Michael R. Thomas, Michael Joseph Murphy
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Patent number: 10132181Abstract: A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.Type: GrantFiled: January 22, 2018Date of Patent: November 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Curtis C. Cowan, Jorge I. Farah
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Publication number: 20180156053Abstract: A method for cooling a rotatable nozzle includes rotating a curved seal about a seal land while maintaining contact therewith. Cooling air is directed through a first diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered. Cool air is directed through a second diffusion hole in the curved seal to cool the nozzle if the rotatable curved seal is in a first position where higher heat is encountered and if in a second position where relatively lower heat is encountered.Type: ApplicationFiled: January 22, 2018Publication date: June 7, 2018Inventors: Curtis C. Cowan, Jorge I. Farah
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Patent number: 9932845Abstract: A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.Type: GrantFiled: June 30, 2011Date of Patent: April 3, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Curtis C. Cowan, Jorge I. Farah
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Patent number: 9803557Abstract: A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.Type: GrantFiled: January 20, 2015Date of Patent: October 31, 2017Assignee: United Technologies CorporationInventors: Jorge I. Farah, Donald W. Peters, Adam Covino, Curtis C. Cowan, James R. Harders, Nicholas W. Kantany
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Publication number: 20160208714Abstract: A blocker door assembly which may be for a cooling system that may be applied to a gas turbine engine includes a plurality of blocker doors circumferentially spaced about an engine axis. Each blocker door is constructed and arranged to move in a circumferential direction to, at least in-part, control air flow through a passage in an adjacent fixture. A sync-ring is concentrically located about the engine axis, disposed in an annular first duct in direct communication with each passage, and engaged to each one of the plurality of blocker doors for simultaneous operation. The sync-ring is aero-dynamically shaped to reduce surrounding airflow resistance.Type: ApplicationFiled: January 20, 2015Publication date: July 21, 2016Inventors: Jorge I. Farah, Donald W. Peters, Adam Covino, Curtis C. Cowan, James R. Harders, Nicholas W. Kantany
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Publication number: 20130001319Abstract: A nozzle liner for a rotatable nozzle includes a seal land and a rotatable seal for moving with the nozzle. The seal has a first diffusion hole for distributing cooling air if the rotatable seal is in a first position and a second diffusion hole for distributing cooling air if the rotatable seal is in a first position and if in a second position.Type: ApplicationFiled: June 30, 2011Publication date: January 3, 2013Inventors: Curtis C. Cowan, Jorge I. Farah
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Patent number: 8205454Abstract: A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.Type: GrantFiled: February 6, 2007Date of Patent: June 26, 2012Assignee: United Technologies CorporationInventors: Curtis C. Cowan, James P. Allore, Paul Attridge
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Patent number: 8186164Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.Type: GrantFiled: August 30, 2011Date of Patent: May 29, 2012Assignee: United Technologies CorporationInventor: Curtis C. Cowan
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Publication number: 20110308254Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.Type: ApplicationFiled: August 30, 2011Publication date: December 22, 2011Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: Curtis C. Cowan
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Patent number: 8020386Abstract: A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link.Type: GrantFiled: August 21, 2007Date of Patent: September 20, 2011Assignee: United Technologies CorporationInventors: Curtis C. Cowan, Robert H. Bush
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Patent number: 8020366Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.Type: GrantFiled: October 9, 2007Date of Patent: September 20, 2011Assignee: United Technologies CorporationInventor: Curtis C. Cowan
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Patent number: 7631481Abstract: A cooled exhaust duct for use in gas turbine engines is provided. The cooled exhaust duct includes an axial centerline, a circumference, an annulus, and a plurality of radially expandable bands. The annulus is disposed between a first wall and a second wall, and extends along the axial centerline. The first wall is disposed radially inside of the second wall. Each of the plurality of radially expandable bands extends circumferentially within the annulus. The bands are axially spaced apart from one another. Each band includes a first portion attached to the first wall, a second portion attached to the second wall and an intermediate portion connected to the first and second portions. The bands create circumferentially extending compartments that inhibit axial travel of the cooling air within the annulus.Type: GrantFiled: December 1, 2004Date of Patent: December 15, 2009Assignee: United Technologies CorporationInventors: Curtis C Cowan, Jorge I. Farah, Debora F. Kehret, Stanley Keysa, Jeffrey R. Lavin, Michael Murphy, Stephen A. Paul, Richard Scott
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Publication number: 20090151358Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.Type: ApplicationFiled: October 9, 2007Publication date: June 18, 2009Applicant: United Technologies CorporationInventor: Curtis C. Cowan
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Publication number: 20090072490Abstract: A nozzle system includes a multitude of circumferentially distributed divergent seals that circumscribe an engine centerline. Each divergent seal includes a multiple of divergent seal intakes adjacent to a joint structure to receive cooling airflow. Each divergent seal body is manufactured of a metallic hot sheet inner skin and a metallic cold sheet outer skin. The skins form a multiple of longitudinal channels which communicate with a multiple of edge channels formed within the first longitudinal side and the second longitudinal side of each divergent seal. The multiple of edge channels are located transverse to the longitudinal axis and are raked aft to facilitate cooling of the gas path surface of each divergent seal and adjacent divergent flaps.Type: ApplicationFiled: February 6, 2007Publication date: March 19, 2009Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Curtis C. Cowan, James P. Allore, Paul Attridge
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Publication number: 20090065610Abstract: A mechanism included in a convergent-divergent nozzle connected to an aftward portion of a gas turbine engine, which mechanism includes at least one actuator configured to be connected to the aftward portion of the engine and to move through one or more positions, a first link pivotally connected to the at least one actuator, a convergent flap pivotally connected to the first link, a divergent flap rotatably connected to the convergent flap and configured to be kinematically connected to an annular ring connected to the at least one actuator, and at least one track configured to extend from the aftward portion of the engine and to movably and pivotally receive the pivotal connection between the convergent flap and the first link.Type: ApplicationFiled: August 21, 2007Publication date: March 12, 2009Applicant: United Technologies CorporationInventors: Curtis C. Cowan, Robert H. Bush
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Patent number: 7377099Abstract: An axisymmetric nozzle for a gas turbine engine has divergent flaps and seals disposed about a central longitudinal axis thereof. The divergent flaps and seals each have an inner surface defining cooling air inlet holes at an upstream portion, cooling air exit holes at a downstream portion, and cooling air channels disposed within the divergent flap and seal, and communicating at a first end with the inlet holes and at a second end with the exit holes for conducting cooling air therethrough. Some of the exit holes of the divergent flap are disposed along lateral edge regions thereof. The divergent seals are interposed between adjacent divergent flaps, and each include lateral edge regions extending laterally beyond the exit holes. The lateral edge regions of each divergent seal have an outer surface overlying at least a portion of the exit holes of an adjacent divergent flap.Type: GrantFiled: May 27, 2005Date of Patent: May 27, 2008Assignee: United Technologies CorporationInventors: Curtis C. Cowan, Stephen A. Paul, Meggan Harris, Paul Attridge
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Patent number: 7337614Abstract: A gas turbine engine is piloted with a pilot flow of fuel delivered to a combustor as a liquid. A first additional flow of the fuel is also delivered to the combustor as a liquid. A second additional flow of the fuel is vaporized and delivered to the combustor as a vapor. A fuel injector may have passageways associated with each of the three flows.Type: GrantFiled: July 18, 2005Date of Patent: March 4, 2008Assignee: United Technologies CorporationInventor: Curtis C. Cowan