Patents by Inventor Bryan P. Dube
Bryan P. Dube 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: 10975706Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle ? with respect to an outer platform surface.Type: GrantFiled: January 17, 2019Date of Patent: April 13, 2021Assignee: Raytheon Technologies CorporationInventors: Bryan H. Farrar, Andrew J. Lazur, Howard J. Liles, Bryan P. Dube
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Patent number: 10808549Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.Type: GrantFiled: July 31, 2018Date of Patent: October 20, 2020Assignee: RAYTHEON TECHNOLOGIES CORPORATIONInventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Dominic J. Mongillo, Jr.
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Publication number: 20200232332Abstract: A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle ? with respect to an outer platform surface.Type: ApplicationFiled: January 17, 2019Publication date: July 23, 2020Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Bryan H. Farrar, Andrew J. Lazur, Howard J. Liles, Bryan P. Dube
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Publication number: 20200158018Abstract: An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.Type: ApplicationFiled: November 21, 2018Publication date: May 21, 2020Inventors: Adam P. Generale, Bryan P. Dube
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Patent number: 10533445Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.Type: GrantFiled: August 23, 2016Date of Patent: January 14, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Anton G. Banks, Christopher Corcoran, Bryan P. Dube
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Patent number: 10526905Abstract: An asymmetric vane assembly includes a high count vane section including a first plurality of vanes oriented in a first position. The asymmetric vane assembly also includes a low count vane section including a second plurality of vanes oriented in a second position, a total number of vanes in the first plurality of vanes being greater than a total number of vanes in the second plurality of vanes, and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.Type: GrantFiled: March 29, 2017Date of Patent: January 7, 2020Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew B. Estes, Bryan P. Dube
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Publication number: 20190360348Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.Type: ApplicationFiled: August 8, 2019Publication date: November 28, 2019Inventors: Jesse M. Carr, Bryan P. Dube, Shelton O. Duelm
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Patent number: 10465540Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.Type: GrantFiled: October 9, 2018Date of Patent: November 5, 2019Assignee: United Technologies CorporationInventors: Jesse M. Carr, Bryan P. Dube
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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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Patent number: 10465543Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.Type: GrantFiled: November 13, 2017Date of Patent: November 5, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Lane Thornton
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Patent number: 10392951Abstract: A vane assembly includes inner and outer rings, a plurality of segmented vane structures circumferentially-spaced around a central axis and between the inner and outer rings, and at least one spring that mechanically traps the segmented vane structures in radial compression between the inner and outer rings.Type: GrantFiled: September 30, 2015Date of Patent: August 27, 2019Assignee: United Technologies CorporationInventors: Jesse M. Carr, Bryan P. Dube, Shelton O. Duelm
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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: 20190093490Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.Type: ApplicationFiled: October 9, 2018Publication date: March 28, 2019Inventors: Jesse M. Carr, Bryan P. Dube
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Publication number: 20180355731Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.Type: ApplicationFiled: July 31, 2018Publication date: December 13, 2018Inventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Dominic J. Mongillo, JR.
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Patent number: 10107117Abstract: An airfoil assembly includes at least one airfoil that has a hollow interior. First and second platforms are disposed between the airfoil. At least one tie-spar extends along an axis through the first platform, the hollow interior of the airfoil, and the second platform. There is a thermal expansion difference between a thermal expansion of the tie-spar in the axial direction and the combined thermal expansion of the airfoil and the first and second platform in the axial direction. At least one spacer portion is arranged on the tie-spar. The spacer portion has a thermal expansion in the axial direction that is greater than the thermal expansion difference such that the spacer portion maintains the tie-spar under tension and clamps the first and second platforms on the airfoil.Type: GrantFiled: August 28, 2015Date of Patent: October 23, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jesse M. Carr, Bryan P. Dube
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Publication number: 20180283189Abstract: An asymmetric vane assembly includes a high count vane section including a first plurality of vanes oriented in a first position. The asymmetric vane assembly also includes a low count vane section including a second plurality of vanes oriented in a second position, a total number of vanes in the first plurality of vanes being greater than a total number of vanes in the second plurality of vanes, and each vane of the high count vane section and each vane of the low count vane section having substantially similar internal core geometry.Type: ApplicationFiled: March 29, 2017Publication date: October 4, 2018Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Matthew B. Estes, Bryan P. Dube
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Patent number: 10072516Abstract: A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil.Type: GrantFiled: August 28, 2015Date of Patent: September 11, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jesse M. Carr, Bryan P. Dube
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Patent number: 10041357Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.Type: GrantFiled: January 20, 2015Date of Patent: August 7, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Dominic J. Mongillo, Jr.
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Publication number: 20180066532Abstract: An assembly for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, an airfoil including a radial end, a first passageway having an outlet at the radial end, and a second passageway having an inlet at the radial end. The assembly further includes a cover having at least one turning cavity configured to direct fluid expelled from the outlet of the first passageway into the inlet of the second passageway.Type: ApplicationFiled: November 13, 2017Publication date: March 8, 2018Inventors: Benjamin F. Hagan, Ryan Alan Waite, Bryan P. Dube, Lane Thornton
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Publication number: 20180058236Abstract: A rim seal for a rotor of a gas turbine engine includes a seal portion extending circumferentially across a rim cavity of a rotor, the sealing portion configured to seal the rim cavity and a first foot portion extending radially inwardly from a first end of the sealing portion. A rotor assembly for a gas turbine engine includes a rotor disc and a plurality of rotor blades secured to the rotor disc defining a rim cavity between the rotor disc and a rim portion of the plurality of rotor blades. A rim seal is located in the rim cavity and includes a seal portion extending circumferentially across the rim cavity, the sealing portion configured to seal the rim cavity. The seal portion has an increasing radial thickness with increasing distance from a first end of the rim seal and from a second end opposite the first end.Type: ApplicationFiled: August 23, 2016Publication date: March 1, 2018Inventors: Anton G. Banks, Christopher Corcoran, Bryan P. Dube