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).

  • Patent number: 12258881
    Abstract: A turbine section for a gas turbine engine includes inner and outer diameter ceramic matrix composite (CMC) support rings that define a gaspath there between. Each of the inner and outer diameter CMC support rings are monolithic and continuous. CMC vane arc segments are disposed in the gaspath and supported by the inner and outer diameter CMC support rings. Each of the CMC vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter CMC support rings with the CMC vane arc segments to retain the CMC vane arc segments between the inner and outer diameter CMC support rings.
    Type: Grant
    Filed: March 7, 2024
    Date of Patent: March 25, 2025
    Assignee: RTX CORPORATION
    Inventors: Howard J. Liles, Bryan P. Dube
  • Patent number: 12241387
    Abstract: An article includes a ceramic matrix composite (CMC) vane arc segment for disposal about an engine central axis. The CMC vane arc segment includes first and second platforms and an airfoil section that extends therebetween. The airfoil section defines a radial stacking axis that is oblique to a Z-axis that is perpendicular to the engine central axis such that the radial stacking axis forms a non-zero angle with the Z-axis.
    Type: Grant
    Filed: August 24, 2023
    Date of Patent: March 4, 2025
    Assignee: RTX CORPORATION
    Inventors: Howard J. Liles, Cheng Gao, Bryan P. Dube
  • Publication number: 20250067188
    Abstract: An article includes a ceramic matrix composite (CMC) vane arc segment for disposal about an engine central axis. The CMC vane arc segment includes first and second platforms and an airfoil section that extends therebetween. The airfoil section defines a radial stacking axis that is oblique to a Z-axis that is perpendicular to the engine central axis such that the radial stacking axis forms a non-zero angle with the Z-axis.
    Type: Application
    Filed: August 24, 2023
    Publication date: February 27, 2025
    Inventors: Howard J. Liles, Cheng Gao, Bryan P. Dube
  • Patent number: 12180857
    Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.
    Type: Grant
    Filed: April 21, 2023
    Date of Patent: December 31, 2024
    Assignee: RTX CORPORATION
    Inventors: Emma J. Place, Bryan P. Dube, Pedro D. Laureano, Bernard Joseph Reilly, III, Mohamed Hassan, Edwin Otero, Andrew Correia, William R. Hackbarth, II, Jeffrey M. Jacques
  • Patent number: 12173621
    Abstract: A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.
    Type: Grant
    Filed: June 4, 2021
    Date of Patent: December 24, 2024
    Assignee: RTX CORPORATION
    Inventors: Bryan P. Dube, Joshua S. Lieberman
  • Patent number: 12163446
    Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.
    Type: Grant
    Filed: March 22, 2023
    Date of Patent: December 10, 2024
    Assignee: RTX CORPORATION
    Inventors: Jon E. Sobanski, Howard J. Liles, Bryan P. Dube, Wojciech Lipka
  • Publication number: 20240352861
    Abstract: An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.
    Type: Application
    Filed: April 21, 2023
    Publication date: October 24, 2024
    Inventors: Emma J. Place, Bryan P. Dube, Pedro D. Laureano, Bernard Joseph Reilly, III, Mohamed Hassan, Edwin Otero, Andrew Correia, William R. Hackbarth, II, Jeffrey M. Jacques
  • Patent number: 12071864
    Abstract: A gas turbine engine includes a turbine section disposed about an engine axis. The turbine section includes inner and outer diameter ceramic support rings that define a gaspath there between. Each of the inner and outer diameter ceramic support rings is monolithic and continuous. Ceramic vane arc segments are disposed in the gaspath and supported by the inner and outer diameter ceramic support rings. Each of the ceramic vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter ceramic support ring with the ceramic vane arc segments to retain the ceramic vane arc segments between the inner and outer diameter ceramic support rings.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: August 27, 2024
    Assignee: RTX CORPORATION
    Inventors: Howard J. Liles, Bryan P. Dube
  • Publication number: 20240247592
    Abstract: A turbine section for a gas turbine engine includes inner and outer diameter ceramic matrix composite (CMC) support rings that define a gaspath there between. Each of the inner and outer diameter CMC support rings are monolithic and continuous. CMC vane arc segments are disposed in the gaspath and supported by the inner and outer diameter CMC support rings. Each of the CMC vane arc segments includes inner and outer platforms and an airfoil section there between. At least one retainer engages the inner or outer diameter CMC support rings with the CMC vane arc segments to retain the CMC vane arc segments between the inner and outer diameter CMC support rings.
    Type: Application
    Filed: March 7, 2024
    Publication date: July 25, 2024
    Inventors: Howard J. Liles, Bryan P. Dube
  • Patent number: 12025020
    Abstract: A vane system includes a plurality of vane assemblies and a continuous support ring. The vane assemblies are arranged circumferentially about an axis and each include a hollow airfoil fairing and a spar. The spar has a spar flange and a spar leg extending radially inwardly from the spar flange and through the hollow airfoil fairing. The continuous support ring has radially inner and outer sides and defines a circumferential row of through-holes between the radially inner and outer sides. The spar legs extend through the through-holes and the spar flanges are affixed at the radially outer side of the continuous support ring.
    Type: Grant
    Filed: May 1, 2023
    Date of Patent: July 2, 2024
    Assignee: RTX Corporation
    Inventors: Robert A. White, III, Bryan P. Dube
  • Patent number: 12012866
    Abstract: An airfoil for a gas turbine engine is configured to extend in a radial direction relative to an engine axis from an inner diameter to an outer diameter. The airfoil comprises a body having a base disposed at the inner diameter, a tip disposed at the outer diameter, a leading edge, a trailing edge, and pressure and suction side walls extending between the leading edge and the trailing edge and between the base and the tip. The body defines an interior cavity. A first wall is disposed in the interior cavity, extends radially, and adjoins the pressure side wall and the suction side wall to form a first cooling channel. A first hole through the first wall connects the first cooling channel to a second cooling channel. The first hole has a profile that tapers inward toward the base.
    Type: Grant
    Filed: June 12, 2023
    Date of Patent: June 18, 2024
    Assignee: RTX Corporation
    Inventors: Dana K. Bondarevsky, Christopher Corcoran, Bryan P. Dube, Yuta Yoshimura, David D. Chapdelaine, Christopher Paul Perron
  • Patent number: 12006837
    Abstract: A ceramic matrix composite component includes a ceramic matrix composite wall; a coating disposed on the wall; and a cooling hole formed in the wall. The cooling hole has a metering section defined along a first axis and a diffuser section defined along a second axis that is offset from the first axis. The cooling hole has a total length defined along the first axis, the total length being the sum of a length of the metering portion and a length of the diffuser portion. The length of the metering portion is between about 40 percent and about 85 percent of the total length. A ceramic matrix composite airfoil and a method of applying a coating to a ceramic matrix composite component are also disclosed.
    Type: Grant
    Filed: January 28, 2022
    Date of Patent: June 11, 2024
    Assignee: RTX Corporation
    Inventors: Bryan P. Dube, David A. Litton
  • Patent number: 12006845
    Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and an airfoil section therebetween. The airfoil section has a pressure side, a suction side, and an internal cavity. The first fairing platform defines suction and pressure side circumferential mate faces, forward and aft faces, a gaspath side, a non-gaspath side, and a flange that projects from the non-gaspath side. The flange extends along one of the suction or pressure side circumferential mate faces. There is a rib that has a rib section in the internal cavity that spans the pressure and suction sides and a rib extension section that extends from the rib section in the internal cavity and along the non-gaspath side of the first fairing platform. The rib extension intersects the flange to form a gusset for reinforcing the flange.
    Type: Grant
    Filed: December 23, 2022
    Date of Patent: June 11, 2024
    Assignee: RTX CORPORATION
    Inventors: Jon E. Sobanski, Bryan P. Dube
  • Patent number: 12000288
    Abstract: A flow path component assembly includes a flow path component that has a platform that extends from a first circumferential side to a second circumferential side. The platform has a first radius of curvature between the first circumferential side and the second circumferential side. A coating is arranged on a portion of the platform near the first circumferential side. The coating has a second radius of curvature. The second radius of curvature is larger than the first radius of curvature.
    Type: Grant
    Filed: May 3, 2021
    Date of Patent: June 4, 2024
    Assignee: RTX CORPORATION
    Inventors: Robert A. White, III, Bryan P. Dube, Wojciech Lipka
  • Publication number: 20240175368
    Abstract: A method of coating a seal slot includes applying a coating to a slot in a component and machining the coating to provide an open height configured to receive a seal. After the machining a surface roughness of the coating is less than about 100 ra. A scaling assembly is also disclosed.
    Type: Application
    Filed: November 29, 2022
    Publication date: May 30, 2024
    Inventors: Raymond Surace, Robert A. White, III, Howard J. Liles, Bryan P. Dube
  • Publication number: 20240175372
    Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.
    Type: Application
    Filed: November 29, 2022
    Publication date: May 30, 2024
    Applicant: Raytheon Technologies Corporation
    Inventors: Robert A. White, III, Raymond Surace, Howard J. Liles, Bryan P. Dube
  • Patent number: 11988104
    Abstract: A plurality of static stator vane are circumferentially spaced in a row axially intermediate the rows of turbine blades. Each stator vane has at least an outer platform with mount structure. Each of the stator vanes are formed of composite materials. The mount structure is provided with sacrificial material. At least a first of the stator vanes is circumferentially adjacent to a second of the stator vanes. An orientation of the first of the stator vanes is re-staggered relative to the second of the stator vanes. The sacrificial material of the first of the stator vanes is machined away such that a final trailing edge of the first of the stator vanes mount structure is now better axially aligned with the trailing edge of the second of the stator vanes mount structure trailing edge.
    Type: Grant
    Filed: November 29, 2022
    Date of Patent: May 21, 2024
    Assignee: RTX Corporation
    Inventors: Robert A. White, III, Raymond Surace, Howard J. Liles, Bryan P. Dube
  • Patent number: 11976568
    Abstract: Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The ceramic matrix composite shell comprises a fibrous preform. The fibrous core has a greater porosity than the fibrous preform. A method of making the ceramic matrix component is also disclosed.
    Type: Grant
    Filed: April 10, 2023
    Date of Patent: May 7, 2024
    Assignee: RTX CORPORATION
    Inventors: Michael G. McCaffrey, Bryan P. Dube
  • Patent number: 11898450
    Abstract: 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: Grant
    Filed: May 18, 2021
    Date of Patent: February 13, 2024
    Assignee: RTX CORPORATION
    Inventors: Raymond Surace, San Quach, Bryan P. Dube
  • Publication number: 20240018875
    Abstract: A vane arc segment includes an airfoil fairing that has first and second fairing platforms and a hollow airfoil section that extends there between. A spar has a spar platform adjacent the first fairing platform and a spar leg that extends from the spar platform and through the hollow airfoil section. The spar leg has an end portion that is distal from the spar platform and that protrudes from the second fairing platform. The end portion has a clevis mount. There is a support platform adjacent the second fairing platform. The support platform has a through-hole through which the end portion of the spar leg extends such that the clevis mount protrudes from the support platform. A pin extends though the clevis mount and locks the support platform to the spar leg such that the airfoil fairing is trapped between the spar platform and the support platform.
    Type: Application
    Filed: March 22, 2023
    Publication date: January 18, 2024
    Inventors: Jon E. Sobanski, Howard J. Liles, Bryan P. Dube, Wojciech Lipka