Patents by Inventor Dennis M. Moura

Dennis M. Moura 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: 11371703
    Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection feature integrally formed in the first component and fluidly connecting a flow path located proximate to the second surface of first component to the cooling channel, the lateral flow injection feature being configured to direct airflow from the airflow path through a passageway and into the cooling channel at least partially in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
    Type: Grant
    Filed: January 4, 2019
    Date of Patent: June 28, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11359810
    Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface; a threaded stud including a first end and a second end opposite the first end, the threaded stud extending from the second surface of the first component; and a faired body operably secured to the threaded stud, wherein the faired body is shaped to redirect the airflow in a lateral direction parallel to the second surface of the first component such that a cross flow is generated.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: June 14, 2022
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11287132
    Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
    Type: Grant
    Filed: February 24, 2020
    Date of Patent: March 29, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
  • Publication number: 20210348761
    Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.
    Type: Application
    Filed: July 20, 2021
    Publication date: November 11, 2021
    Applicant: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dennis M. Moura
  • Patent number: 11143401
    Abstract: A gas turbine engine component comprising: a first component having a receiving aperture extending; a second component having a first surface and a second surface; and a passageway portion including a first end, a second end opposite the first end, and an outer surface extending from the second end to the first end, the passageway portion extending from the second surface of the second component through the receiving aperture of the first component, wherein the outer surface of the passageway portion and the first component define a gap therebetween, the gap fluidly connecting airflow in an airflow path proximate the second surface of the first component to the cooling channel, wherein the gap is configured to direct the airflow along the outer surface and the outer surface is shaped to redirect the airflow in a lateral direction parallel to the second surface such that a lateral airflow is generated.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: October 12, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11098653
    Abstract: A gas turbine engine component assembly is provided. The gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface wherein the first component includes a cooling hole extending from the second surface to the first surface through the first component; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a deflector forming a passageway with the second surface of the first component, the passageway configured to direct airflow into the cooling channel in a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
    Type: Grant
    Filed: January 7, 2019
    Date of Patent: August 24, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11098899
    Abstract: A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: August 24, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Dennis M Moura
  • Patent number: 11092339
    Abstract: A gas turbine engine component assembly comprising: a first component having a first surface and a second surface opposite the first surface, wherein the first component includes a cooling hole extending from the second surface to the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining a cooling channel therebetween; and a lateral flow injection device secured to first component, the lateral flow injection device fluidly connecting a flow path located proximate to the second surface of the first component to the cooling channel, the lateral flow injection device being configured to direct airflow from the airflow path into the cooling channel in about a lateral direction parallel to the second surface of the second component such that a cross flow is generated in the cooling channel.
    Type: Grant
    Filed: January 4, 2019
    Date of Patent: August 17, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Dennis M. Moura, Carey Clum
  • Patent number: 11041391
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.
    Type: Grant
    Filed: April 20, 2020
    Date of Patent: June 22, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
  • Patent number: 11015464
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
    Type: Grant
    Filed: January 24, 2020
    Date of Patent: May 25, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
  • Patent number: 10934890
    Abstract: A shrouded conduit is provided for arranging, for example, in a gas path of a turbine engine. The shrouded conduit includes a tubular shroud extending longitudinally along a centerline. The shrouded conduit also includes a fluid conduit extending longitudinally in the shroud. A first portion of the fluid conduit is connected laterally to and may be formed integral with a first portion of the shroud.
    Type: Grant
    Filed: May 8, 2015
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Joe Ott, Dennis M. Moura, Stanley J. Funk, Shawn Stempinski, Roger O. Coffey, John J. Rup, Jr., Lexia Kironn, Gary A. Schirtzinger
  • Patent number: 10878556
    Abstract: A method of assessing damage to a component includes displaying a sensor image of the component in a first viewing pane, displaying a reference image of the component, which is a graphical depiction of the component with accurate dimensions, in a second viewing pane, placing a plurality of first identification markers on the sensor image of the component in the first viewing pane to correspond to a matching location with a second identification marker on the component in the reference image, identifying a region of damage on the component in the sensor image, mapping the region of damage to the component in the reference image using the plurality of first and second identification markers, and calculating a size of the region of damage.
    Type: Grant
    Filed: January 19, 2018
    Date of Patent: December 29, 2020
    Assignee: United Technologies Corporation
    Inventors: Paul D. Hestand, Alan Matthew Finn, Dennis M. Moura, Ziyou Xiong, Keith R. Russell
  • Publication number: 20200386106
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.
    Type: Application
    Filed: April 20, 2020
    Publication date: December 10, 2020
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura, David Bitzko, Alex J. Schneider
  • Patent number: 10816206
    Abstract: A combustor for a turbine engine includes an inner liner panel with a multiple of inner dilution passages. The multiple of dilution passages includes a repeating pattern of a first major inner air passage, a minor inner air passage, and a second major inner air passage. A combustor for a turbine engine includes an outer liner panel with a multiple of outer dilution passages. The multiple of outer dilution passages includes a repeating pattern of a first major outer air passage, a first minor outer air passage, a second major outer air passage, and a second minor outer air passage.
    Type: Grant
    Filed: October 20, 2014
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Dennis M. Moura, III, Reza Rezvani
  • Patent number: 10807163
    Abstract: An additively manufactured component includes a heat transfer augmentation feature with a surface finish between about 125-900 micro inches.
    Type: Grant
    Filed: July 14, 2015
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Joe Ott, Stanley J Funk, Roger O Coffey, Shawn Stempinski, John J Rup, Jr., Lyutsia Dautova, Dennis M Moura
  • Patent number: 10808928
    Abstract: A combustor for use in a gas turbine engine has a combustor outer shell. A panel has an inner face which will face hot products of combustion, and a boss surrounding a feature, with the boss extending to an outer end. A spacing surface is spaced from the boss, and is at an outer position that is inward of the outer end of the boss. The spacing surface spaces the panel from the outer shell. A trough is intermediate the boss and the spacing surface. The trough extends to an outer end which is inward of the outer position of the spacing surface. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: August 6, 2014
    Date of Patent: October 20, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Lee Edward Bouldin, Monica Pacheco-Tougas, Dennis M. Moura, Jonathan Jeffery Eastwood
  • Publication number: 20200300389
    Abstract: A method is provided involving an additive manufacturing system. This method includes a step of forming a first fluid conduit using the additive manufacturing system. The method also includes a step of providing a fluid coupling. The fluid coupling includes the first fluid conduit and a second fluid conduit. The first fluid conduit is connected to and fluidly coupled with the second fluid conduit. The first fluid conduit has a first configuration. The second fluid conduit has a second configuration that is different than the first configuration.
    Type: Application
    Filed: June 11, 2020
    Publication date: September 24, 2020
    Inventors: Joe Ott, Dennis M. Moura, Stanley J. Funk, Shawn Stempinski, Roger O. Coffey, John J. Rup, JR., Lexia Kironn, Gary A. Schirtzinger
  • Publication number: 20200292172
    Abstract: An assembly for a turbine engine includes a combustor wall. The combustor wall includes a shell, a heat shield and an annular land. The heat shield is attached to the shell. The land extends vertically between the shell and the heat shield. The land extends laterally between a land outer surface and an inner surface, which at least partially defines a quench aperture in the combustor wall. A lateral distance between the land outer surface and the inner surface varies around the quench aperture.
    Type: Application
    Filed: February 24, 2020
    Publication date: September 17, 2020
    Inventors: Dennis M. Moura, Jonathan J. Eastwood, Lee E. Bouldin, Monica Pacheco-Tougas
  • Publication number: 20200277867
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
    Type: Application
    Filed: January 24, 2020
    Publication date: September 3, 2020
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura
  • Patent number: 10738701
    Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A combustor assembly and method are also disclosed.
    Type: Grant
    Filed: August 30, 2017
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Steven D. Porter, Shawn M. McMahon, Kevin Zacchera, Noah Wadsworth, Christopher Whitfield, Sean D. Bradshaw, Dennis M. Moura