Patents by Inventor Ky H. VU
Ky H. VU 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: 11415020Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.Type: GrantFiled: December 4, 2019Date of Patent: August 16, 2022Assignee: Raytheon Technologies CorporationInventors: Ky H. Vu, Brian R. Pelletier
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Patent number: 11131212Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.Type: GrantFiled: December 6, 2017Date of Patent: September 28, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
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Publication number: 20210172335Abstract: A gas turbine engine includes a primary flowpath connecting a compressor section, a combustor section and a turbine section. The turbine section includes a stage vane having a radially outward platform and a vane extending into the primary flowpath. The platform includes a cooling plenum. At least one retaining feature extends radially outward from the platform. At least one vectored cooling hole is disposed in the retaining feature and is configured to direct cooling air from the plenum to an adjacent gaspath component.Type: ApplicationFiled: December 4, 2019Publication date: June 10, 2021Inventors: Ky H. Vu, Brian R. Pelletier
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Patent number: 10968746Abstract: A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.Type: GrantFiled: October 12, 2018Date of Patent: April 6, 2021Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Ky H. Vu, Dominic J. Mongillo
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Patent number: 10822962Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.Type: GrantFiled: September 27, 2018Date of Patent: November 3, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Ky H. Vu, Adam P. Generale
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Patent number: 10648351Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.Type: GrantFiled: December 6, 2017Date of Patent: May 12, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
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Patent number: 10619492Abstract: A vane for a gas turbine engine may comprise a vane platform and an airfoil extending radially from the vane platform. The airfoil may comprise an inlet defined, at least partially, by an internal surface of the airfoil. The internal surface may comprise a convex curve proximate the inlet. A transition between an external surface of the airfoil and a surface of the vane platform may comprise a concave curve. A radius of curvature of the convex curve of the internal surface may be concentric to a radius of curvature of the concave curve of the transition.Type: GrantFiled: December 11, 2017Date of Patent: April 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Ky H. Vu, Adam P. Generale, Brandon L. Howard
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Publication number: 20200102838Abstract: A platform for an airfoil of a gas turbine engine having an axis extending from a front of the gas turbine engine to a rear of the gas turbine engine. The platform includes a leading edge configured to face towards the front of the gas turbine engine. The platform further includes a trailing edge opposite the leading edge. The platform further includes a radially outer surface that defines a pocket for receiving a cooling airflow. The platform further includes a cover coupled to the radially outer surface to at least partially enclose the pocket and defining a plurality of air inlet holes configured to port at least a portion of the cooling airflow into the pocket.Type: ApplicationFiled: September 27, 2018Publication date: April 2, 2020Applicant: United Technologies CorporationInventors: KY H. VU, Adam P. Generale
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Publication number: 20200088038Abstract: A stator vane assembly including an inner diameter platform. The assembly also includes an outer diameter platform defining an air inlet orifice extending radially therethrough. Further included is an airfoil extending between the inner diameter platform and the outer diameter platform, the airfoil having a hollow portion therein defining a serpentine cooling airflow path fluidly coupled to the air inlet orifice. Yet further included is a collar extending radially outwardly from the outer diameter platform and positioned adjacent the air inlet orifice, the collar extending to a non-uniform radial distance. The assembly also includes a turn cover operatively coupled to the collar.Type: ApplicationFiled: October 12, 2018Publication date: March 19, 2020Inventors: Ky H. Vu, Dominic J. Mongillo
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Patent number: 10465559Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.Type: GrantFiled: December 13, 2017Date of Patent: November 5, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Ky H. Vu, Bryan P. Dube, Michael J. Allen
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Publication number: 20190178107Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.Type: ApplicationFiled: December 13, 2017Publication date: June 13, 2019Inventors: Ky H. Vu, Bryan P. Dube, Michael J. Allen
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Publication number: 20190178091Abstract: A vane for a gas turbine engine may comprise a vane platform and an airfoil extending radially from the vane platform. The airfoil may comprise an inlet defined, at least partially, by an internal surface of the airfoil. The internal surface may comprise a convex curve proximate the inlet. A transition between an external surface of the airfoil and a surface of the vane platform may comprise a concave curve. A radius of curvature of the convex curve of the internal surface may be concentric to a radius of curvature of the concave curve of the transition.Type: ApplicationFiled: December 11, 2017Publication date: June 13, 2019Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Ky H. Vu, Adam P. Generale, Brandon L. Howard
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Publication number: 20190170014Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes a serpentine cavity and a serpentine turn extends from the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge at least partially defines a fluid passageway with the serpentine turn.Type: ApplicationFiled: December 6, 2017Publication date: June 6, 2019Inventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
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Publication number: 20190170002Abstract: A component for a gas turbine engine includes a platform that has a gas path side and a non-gas path side. At least one airfoil extends from the gas path side of the platform. At least one airfoil includes an internal cavity that has an inlet on the non-gas path side of the platform. A cover plate is located adjacent the non-gas path side of the platform. The cover plate includes a first plurality of fluid openings that extend through the cover plate. At least one bulge is at least partially aligned with the inlet.Type: ApplicationFiled: December 6, 2017Publication date: June 6, 2019Inventors: Brandon W. Spangler, Adam P. Generale, Ky H. Vu
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Patent number: 10280793Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform, an airfoil that extends from the platform, and an insert positioned such that a first portion of the insert extends relative to a surface of the platform and a second portion extends inside the airfoil. A standoff supports the insert above the surface.Type: GrantFiled: August 28, 2014Date of Patent: May 7, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventor: Ky H. Vu
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Patent number: 10280761Abstract: A component for use in a gas turbine engine comprises a body and a micro-core cooling circuit embedded within the body. The micro-core circuit has a variation in either the thickness or contoured surface, away from a generally planar shape to a non-planar shape.Type: GrantFiled: October 1, 2015Date of Patent: May 7, 2019Assignee: United Technologies CorporationInventors: Ky H. Vu, Brandon W. Spangler
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Patent number: 10047617Abstract: An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. An airfoil component for a gas turbine engine includes a platform. The airfoil component includes a flow path surface from which an airfoil extends. A laterally extending aft surface is adjacent to the flow path surface. A contoured surface adjoins the flow path surface and the aft surface. The aft surface extends from a first aft edge to a second aft edge at a circumferentially extending edge. The contoured surface is arranged inboard from at least one of the first and second edges.Type: GrantFiled: April 7, 2014Date of Patent: August 14, 2018Assignee: United Technologies CorporationInventors: Ky H. Vu, Lisa P. O'Neill, Takao Fukuda, Gerald M. Mace, Jr., Andy Turko, Andrew P. Boursy, Lynn M. Boy
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Patent number: 10041374Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.Type: GrantFiled: March 23, 2015Date of Patent: August 7, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Brandon W. Spangler, Ky H. Vu, Gina Cavallo
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Patent number: 9771814Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.Type: GrantFiled: March 9, 2015Date of Patent: September 26, 2017Assignee: United Technologies CorporationInventors: Brandon W. Spangler, Ky H. Vu, Jeffrey J. DeGray, Ryan Alan Waite, Gina Cavallo, Thomas P. Dziuba
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Publication number: 20160265372Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.Type: ApplicationFiled: March 9, 2015Publication date: September 15, 2016Inventors: Brandon W. Spangler, Ky H. Vu, Jeffrey J. DeGray, Ryan Alan Waite, Gina Cavallo, Thomas P. Dziuba