Patents by Inventor Gary J. Dillard
Gary J. Dillard 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: 20240159398Abstract: An assembly is provided for a gas turbine engine. This engine assembly includes a fuel injector assembly, and the fuel injector assembly includes a fuel swirler and an air swirler. The fuel swirler is configured to swirl fuel in a direction about the axis to provide swirled fuel. The fuel injector assembly is configured to inject the swirled fuel as an annular fuel flow along an axis. The air swirler is configured to swirl air in the direction about the axis to provide swirled air. The fuel injector assembly is configured to inject the swirled air as an annular air flow along the axis, adjacent and circumscribing the annular fuel flow.Type: ApplicationFiled: November 13, 2022Publication date: May 16, 2024Inventors: Zhongtao Dai, Wookyung Kim, Stephen K. Kramer, Baris A. Sen, Gary J. Dillard
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Patent number: 11698192Abstract: A combustor liner assembly includes a first liner panel that has a first forward end and a first aft end. A second liner panel has a second forward end and a second aft end. A support band has a plurality of circumferentially spaced holes. The support band is arranged between the first liner panel and the second liner panel. The support band has a protrusion with a first angled surface and a second angled surface. The first angled surface is in engagement with the first aft end and the second angled surface in engagement with the second forward end.Type: GrantFiled: April 6, 2021Date of Patent: July 11, 2023Assignee: Raytheon Technologies CorporationInventors: Salvatore D'Alessandro, Gary J. Dillard
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Publication number: 20220316707Abstract: A combustor liner assembly includes a first liner panel that has a first forward end and a first aft end. A second liner panel has a second forward end and a second aft end. A support band has a plurality of circumferentially spaced holes. The support band is arranged between the first liner panel and the second liner panel. The support band has a protrusion with a first angled surface and a second angled surface. The first angled surface is in engagement with the first aft end and the second angled surface in engagement with the second forward end.Type: ApplicationFiled: April 6, 2021Publication date: October 6, 2022Inventors: Salvatore D'Alessandro, Gary J. Dillard
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Patent number: 11268696Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.Type: GrantFiled: October 19, 2018Date of Patent: March 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Gary J. Dillard, Assaf Farah
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Patent number: 11149684Abstract: A heat shield panel for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel includes an inner base layer, an outer base layer, and a grommet having a flange disposed between the inner base layer and the outer base layer.Type: GrantFiled: September 28, 2018Date of Patent: October 19, 2021Assignee: Raytheon Technologies CorporationInventor: Gary J. Dillard
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Patent number: 10816205Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.Type: GrantFiled: May 30, 2018Date of Patent: October 27, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Gary J Dillard, Russell B Hanson
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Patent number: 10801731Abstract: A combustor panel for use in a gas turbine engine includes a body portion having an outwardly curved edge defining a channel between the body portion and the outwardly curved edge. The outwardly curved edge includes a plurality of slots. The panel further includes a fastening member having a base disposed within the channel and a plurality of fasteners extending from the base and disposed within the slots.Type: GrantFiled: September 13, 2018Date of Patent: October 13, 2020Assignee: United Technologies CorporationInventor: Gary J. Dillard
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Publication number: 20200124281Abstract: A combustor for use in a gas turbine engine comprising: an outward shell; an inward shell located radially inward of the outward shell, the inward shell and the outward shell defining a combustion chamber therebetween; an aft outward panel located proximate the outward shell, the aft outward panel extending from an aft end of the combustion chamber to an outward panel joint; an aft inward panel located proximate the inward shell, the aft inward panel extending from the aft end of the combustion chamber to an inward panel joint; and a forward panel located proximate a forward end of the combustion chamber, the forward panel comprising: an outward wall located proximate the outward shell; an inward wall located proximate the inward shell; and a forward wall located proximate the forward end of the combustion chamber, the forward wall extending from the inward wall to the outward wall.Type: ApplicationFiled: October 19, 2018Publication date: April 23, 2020Inventors: Gary J. Dillard, Assaf Farah
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Publication number: 20200102907Abstract: A heat shield panel for use in a combustor of a gas turbine engine is disclosed. In various embodiments, the heat shield panel includes an inner base layer, an outer base layer, and a grommet having a flange disposed between the inner base layer and the outer base layer.Type: ApplicationFiled: September 28, 2018Publication date: April 2, 2020Applicant: United Technologies CorporationInventor: Gary J. Dillard
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Publication number: 20200088410Abstract: A combustor panel for use in a gas turbine engine includes a body portion having an outwardly curved edge defining a channel between the body portion and the outwardly curved edge. The outwardly curved edge includes a plurality of slots. The panel further includes a fastening member having a base disposed within the channel and a plurality of fasteners extending from the base and disposed within the slots.Type: ApplicationFiled: September 13, 2018Publication date: March 19, 2020Inventor: Gary J. Dillard
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Publication number: 20190368737Abstract: A pre-diffuser fairing for a gas turbine engine is disclosed. In various embodiments, the pre-diffuser fairing includes a first side wall, a first radially inward portion and a first radially outward portion and a second side wall, a second radially inward portion and a second radially outward portion. The first side wall and the second side wall are spaced apart to form a cavity configured to receive a strut.Type: ApplicationFiled: May 30, 2018Publication date: December 5, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Gary J. Dillard, Russell B. Hanson
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Patent number: 10378451Abstract: A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.Type: GrantFiled: September 10, 2014Date of Patent: August 13, 2019Assignee: United Technologies CorporationInventor: Gary J. Dillard
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Patent number: 10131010Abstract: A brazed end cover assembly for a gas turbine combustor using Au—Ni braze is disclosed. The end cover assembly may include an end cover with openings, a flow insert, first and second gaps between the end cover and the flow insert, and first and second braze joints formed at the first and second gaps, wherein the braze materials used comprises Au and Ni. A method of brazing a flow insert into an end cover is also disclosed. The method may include providing an end cover and a flow insert with first and second gaps therebetween; applying a braze material to an outer surface of the flow insert, wherein the braze material comprises Au and Ni; inserting the flow insert into the end cover; heating the assembly to a brazing temperature for some time; and cooling the resulting brazed assembly to room temperature.Type: GrantFiled: June 28, 2012Date of Patent: November 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Gary J Dillard
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Publication number: 20160201566Abstract: A seal assembly is provided for a gas turbine engine. This seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed toward a backwall. The seal assembly also includes a faying extension that at least partially extends into the channel and into contact with the bulb. An exhaust duct is also provided for a gas turbine engine. This exhaust duct includes a seal assembly between a first exhaust duct section and a second exhaust duct section. The seal assembly includes a tadpole seal with a bulb and a tail, where the tail is directed upstream.Type: ApplicationFiled: September 10, 2014Publication date: July 14, 2016Inventor: Gary J. Dillard
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Patent number: 9097211Abstract: An example gas turbine engine includes an engine casing and an engine liner within the engine casing. One of the engine casing or the engine liner includes a first attachment structure. The other of the engine casing or the engine liner defines a track guide. A slideable member is moveable within the track guide between an engaged position and a disengaged position. The slideable member includes a second attachment structure engageable with the first attachment structure to secure the engine liner relative the engine casing when the slideable member is in the engaged position.Type: GrantFiled: June 6, 2008Date of Patent: August 4, 2015Assignee: United Technologies CorporationInventors: Gonzalo F. Martinez, Gary J. Dillard
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Publication number: 20140000266Abstract: A brazed end cover assembly for a gas turbine combustor using Au-Ni braze is disclosed. The end cover assembly may include an end cover with openings, a flow insert, first and second gaps between the end cover and the flow insert, and first and second braze joints formed at the first and second gaps, wherein the braze materials used comprises Au and Ni. A method of brazing a flow insert into an end cover is also disclosed. The method may include providing an end cover and a flow insert with first and second gaps therebetween; applying a braze material to an outer surface of the flow insert, wherein the braze material comprises Au and Ni; inserting the flow insert into the end cover; heating the assembly to a brazing temperature for some time; and cooling the resulting brazed assembly to room temperature.Type: ApplicationFiled: June 28, 2012Publication date: January 2, 2014Applicant: Pratt & WhitneyInventor: Gary J Dillard
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Publication number: 20130232949Abstract: An apparatus for minimizing signature of an engine having an exhaust gas path and a fan gas path includes a casing, and a liner disposed within the casing. The exhaust gas path passes within the liner and the fan gas path passes between the liner and the casing. The casing is disconnected into an upstream portion and a downstream portion, each portion in registration with the liner, such that there are minimum pressure imbalances caused by the exhaust gas path, the fan gas path and ambient on the downstream portion.Type: ApplicationFiled: March 9, 2012Publication date: September 12, 2013Inventor: Gary J. Dillard
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Patent number: 8322127Abstract: A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in fluid communication with the convergent portion. A conduit is in communication with a bypass fluid flow. The conduit has a thrust vectoring port located near the divergent portion.Type: GrantFiled: November 1, 2007Date of Patent: December 4, 2012Assignee: United Technologies CorporationInventors: Sean P. Zamora, Michael J. Murphy, Gary J. Dillard, Glenn R. Estes
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Publication number: 20090301093Abstract: An example gas turbine engine includes an engine casing and an engine liner within the engine casing. One of the engine casing or the engine liner includes a first attachment structure. The other of the engine casing or the engine liner defines a track guide. A slideable member is moveable within the track guide between an engaged position and a disengaged position. The slideable member includes a second attachment structure engageable with the first attachment structure to secure the engine liner relative the engine casing when the slideable member is in the engaged position.Type: ApplicationFiled: June 6, 2008Publication date: December 10, 2009Inventors: Gonzalo F. Martinez, Gary J. Dillard
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Publication number: 20090114740Abstract: A nozzle assembly for a turbine engine has a convergent portion for converging fluid flow from a turbine engine core. A divergent portion for diverging fluid flow from the turbine engine core is in fluid communication with the convergent portion. A conduit is in communication with a bypass fluid flow. The conduit has a thrust vectoring port located near the divergent portion.Type: ApplicationFiled: November 1, 2007Publication date: May 7, 2009Inventors: Sean P. Zamora, Michael J. Murphy, Gary J. Dillard, Glenn R. Estes