Patents by Inventor San Quach
San Quach 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: 20240093870Abstract: In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.Type: ApplicationFiled: November 30, 2023Publication date: March 21, 2024Inventors: San Quach, Thomas N. Slavens
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Patent number: 11898450Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.Type: GrantFiled: May 18, 2021Date of Patent: February 13, 2024Assignee: RTX CORPORATIONInventors: Raymond Surace, San Quach, Bryan P. Dube
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Patent number: 11867402Abstract: In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.Type: GrantFiled: March 19, 2021Date of Patent: January 9, 2024Assignee: RTX CorporationInventors: San Quach, Thomas N. Slavens
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Patent number: 11808154Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.Type: GrantFiled: September 26, 2022Date of Patent: November 7, 2023Assignee: RTX CORPORATIONInventors: San Quach, Bryan P. Dube, Erik R. Granstand, Michael G. McCaffrey, Stephen G. Pixton
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Patent number: 11661853Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.Type: GrantFiled: September 23, 2021Date of Patent: May 30, 2023Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Tracy A. Propheter-Hinckley, Steven Bruce Gautschi
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Publication number: 20230057881Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.Type: ApplicationFiled: November 1, 2022Publication date: February 23, 2023Inventors: San Quach, Robert A. White, III, Tyler G. Vincent
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Publication number: 20230036836Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure having an axial portion and a radial portion and an outer portion arranged between the support structure. The outer portion defines a gap between the outer portion and the axial portion of the support structure. A flange is positioned relative to the gap.Type: ApplicationFiled: September 26, 2022Publication date: February 2, 2023Inventors: San Quach, Bryan P. Dube, Erik R. Granstand, Michael G. McCaffrey, Stephen G. Pixton
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Patent number: 11536145Abstract: An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.Type: GrantFiled: April 9, 2021Date of Patent: December 27, 2022Assignee: Raytheon Technologies CorporationInventors: San Quach, Alex J. Schneider
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Publication number: 20220372888Abstract: An assembly for a gas turbine engine includes, among other things, an end wall including a main body extending between a first end portion and a second end portion to establish a seal face. The end wall includes a first attachment portion dimensioned to fixedly attach the main body to a static structure at a first attachment point. An airfoil extends radially inwardly from the end wall relative to an assembly axis. The airfoil includes an inner cavity extending between a first end portion and a second end portion, the first end portion adjacent the end wall of the airfoil. A spar member includes a spar body extending between a first end portion and a second end portion. The spar body extends at least partially through the inner cavity. The first end portion of the end wall is cantilevered from the first attachment point.Type: ApplicationFiled: May 18, 2021Publication date: November 24, 2022Inventors: Raymond Surace, San Quach, Bryan P. Dube
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Patent number: 11499443Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.Type: GrantFiled: December 21, 2020Date of Patent: November 15, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Robert A. White, III, Tyler G. Vincent
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Patent number: 11492914Abstract: A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.Type: GrantFiled: October 27, 2020Date of Patent: November 8, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Adam P. Generale, Raymond Surace, Lucas Dvorozniak
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Patent number: 11486256Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the flange. There is a conformal thermal insulation blanket disposed on the flange.Type: GrantFiled: December 7, 2020Date of Patent: November 1, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Tyler G. Vincent, Cheng Gao, Howard J. Liles
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Patent number: 11473444Abstract: An airfoil includes a ceramic airfoil that defines a leading edge, a trailing edge, a pressure side, a suction side, a first radial end, and a second radial end. The ceramic airfoil section has an internal cavity and a rib that divides the internal cavity into a first radial passage and a second radial passage. The first radial passage is open at both the first radial end and the second radial end, and the second radial passage is open at least at the second radial end. A cooling passage circuit includes a first radial leg through the first radial passage, a second radial leg though the second radial passage, and a turn leg outside of the internal cavity at the second radial end. The turn leg connects the first radial leg and the second radial leg.Type: GrantFiled: November 8, 2019Date of Patent: October 18, 2022Assignee: Raytheon Technologies CorporationInventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Publication number: 20220325630Abstract: An airfoil vane assembly according to an exemplary embodiment of this disclosure, among other possible things includes a vane piece having a first vane platform, a second vane platform, and a hollow airfoil section joining the first vane platform and the second vane platform, a spar piece having a spar platform and a spar extending from the spar platform into the hollow airfoil section, and at least one seal arranged at a sealing surface of the spar platform and sealing between the spar platform and the first vane platform. The airfoil vane assembly also includes a thermal barrier coating disposed on the spar piece. The sealing surface is free from the thermal barrier coating. A gas turbine engine and a method of making a spar piece for an airfoil vane assembly are also disclosed.Type: ApplicationFiled: April 9, 2021Publication date: October 13, 2022Inventors: San Quach, Alex J. Schneider
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Publication number: 20220316353Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.Type: ApplicationFiled: April 2, 2021Publication date: October 6, 2022Inventors: San Quach, Bryan P. Dube, Erik R. Granstand, Michael G. McCaffrey, Stephen G. Pixton
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Patent number: 11454129Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.Type: GrantFiled: April 2, 2021Date of Patent: September 27, 2022Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: San Quach, Bryan P. Dube, Erik R. Granstand, Michael G. McCaffrey, Stephen G. Pixton
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Publication number: 20220299206Abstract: In one exemplary embodiment, a combustor liner includes a first portion extending in a substantially axial direction and a second portion that extending in the substantially axial direction. A step connects the first portion and the second portion. The step is arranged at an angle to the second portion that is less than 90°. The step has a step height defined as a distance between the first portion and the second portion. The first portion, second portion, and step are formed as a unitary ceramic component. A slot extends through the step, and a ratio of a height of the slot to a height of the step is greater than 0.66.Type: ApplicationFiled: March 19, 2021Publication date: September 22, 2022Inventors: San Quach, Thomas N. Slavens
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Patent number: 11415002Abstract: An airfoil includes an vane airfoil, which has a ceramic matrix composite airfoil section including an outer wall that defines an internal cavity. The vane airfoil has an associated temperature profile which defines at least one high temperature area and at least one low temperature area. The vane airfoil includes a first zone which is defined in a first radial extent and corresponds to the high temperature area of the temperature profile and a second zone defined in a second radial extent and corresponds to the low temperature area of the temperature profile. An insert is situated in the internal cavity. The insert includes a first zone defined in a first radial extent that is aligned with the first zone of the vane airfoil. The first zone includes a first plurality of cooling holes which are configured to provide a first cooling density. A second zone is defined in a second radial extent that is aligned with the second zone of the vane airfoil.Type: GrantFiled: October 18, 2019Date of Patent: August 16, 2022Assignee: Raytheon Technologies CorporationInventors: Adam P. Generale, Lucas Dvorozniak, San Quach
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Patent number: 11384654Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.Type: GrantFiled: November 18, 2019Date of Patent: July 12, 2022Assignee: Raytheon Technologies CorporationInventors: Winston Gregory Smiddy, San Quach, Matthew D. Parekh, Jeffrey T. Morton
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Publication number: 20220195879Abstract: A gas turbine engine includes a ceramic wall for bounding an engine core gas path. The ceramic wall has a ceramic wall first side that faces the engine core gas path and a ceramic wall second side that faces away from the engine core gas path. There is a metallic wall adjacent the ceramic wall second side. The metallic wall has a metallic wall first side that faces the ceramic wall and a metallic wall second side that faces away from the ceramic wall. The metallic wall and the ceramic wall are spaced apart such that there is a channel there between. There is a seal on the ceramic wall second side, and the metallic wall has at least one cooling hole adjacent the seal for emitting cooling air to cool the seal.Type: ApplicationFiled: December 21, 2020Publication date: June 23, 2022Inventors: San Quach, Robert A. White, III, Tyler G. Vincent