Patents by Inventor W. Spangler

W. Spangler 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).

  • PLATFORM COVER PLATES FOR GAS TURBINE ENGINE COMPONENTS
    Publication number: 20190330986
    Abstract: Components for gas turbine engines are provided. The components include a platform, a first airfoil extending from the platform, a first cavity located within the first airfoil, the first cavity includes a forward portion and an aft portion separated by a divider, a cover plate attached to the platform on a side opposite the airfoil, wherein a platform cavity is defined between the cover plate and the platform and wherein the first cavity is fluidly connected to the platform cavity through a first cavity inlet, and a first cavity separating rail dividing the platform cavity into a first platform forward cavity and a first platform aft cavity, wherein the first platform forward cavity is fluidly connected to the aft portion of the first cavity and the first platform aft cavity is fluidly connected to the forward portion of the first cavity.
    Type: Application
    Filed: April 25, 2018
    Publication date: October 31, 2019
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • SPIRAL CAVITIES FOR GAS TURBINE ENGINE COMPONENTS
    Publication number: 20190330987
    Abstract: Baffles and airfoils for installation within gas turbine engines are provided. The baffles include a baffle side wall extending between a first end and a second end and a baffle divider within the baffle side wall, wherein the baffle divider and the baffle side wall define a first cavity and a second cavity. The first cavity is located at a first side at the first end and the second cavity is located at a second side at the first end and the baffle divider includes a spiral portion such that the first cavity is transitioned toward the second side and the second cavity is transitioned toward the first side.
    Type: Application
    Filed: April 25, 2018
    Publication date: October 31, 2019
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • Cooling passages for a gas path component of a gas turbine engine
    Patent number: 10458252
    Abstract: A gas path component for a gas turbine engine includes an element configured to be exposed to a gas path. The element includes a plurality of internal cooling passages. At least one of the internal cooling passages includes a cross section having a plurality of asymmetrical filleted corners.
    Type: Grant
    Filed: December 1, 2015
    Date of Patent: October 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Brandon W. Spangler, Atul Kohli
  • Cover plate for a component of a gas turbine engine
    Patent number: 10458291
    Abstract: A component for a gas turbine engine includes a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: October 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Russell J. Bergman
  • Seal arrangement for turbine engine component
    Patent number: 10458264
    Abstract: A component for a gas turbine engine according to an example of the present disclosure includes, among other things, a body including a cold side surface adjacent to a mate face. A plurality of ridges extends from the cold side surface. A seal member abuts the plurality of ridges to define a plurality of cooling passages. The seal member is configured to move between a first position and a second position relative to the plurality of ridges. Each of the plurality of cooling passages includes a first inlet defined at the first position and a second, different inlet defined at the second position. A method of sealing between adjacent components of a gas turbine engine is also disclosed.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: October 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dominic J. Mongillo, Jr., Brandon W. Spangler, Lane Thornton
  • AIRFOILS FOR GAS TURBINE ENGINES
    Publication number: 20190301286
    Abstract: Airfoils for gas turbine engines are provided. The airfoil include an airfoil body, the body extending between a leading edge and a trailing edge in an axial direction and between a pressure side wall and a suction side wall in a circumferential direction, the airfoil body defining an airfoil cavity therein and a baffle located within the airfoil cavity. The airfoil includes increased thickness side walls to form an airfoil cavity to account for the baffle within the cavity and to direct cooling flow through the airfoil.
    Type: Application
    Filed: March 28, 2018
    Publication date: October 3, 2019
    Inventors: Brandon W. Spangler, Corey D. Anderson
  • Baffle insert for a gas turbine engine component and component with baffle insert
    Patent number: 10422233
    Abstract: A component of a gas turbine engine having: an internal cooling cavity; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; at least one separating feature located between a pair of ends of a pair of the plurality of trip strips, wherein the plurality of trip strips and the at least one separating feature are spaced from an interior surface of the internal cooling cavity; a plurality of trip strips extending upwardly from the interior surface; and at least one separating feature located between a pair of ends of the plurality of trip strips located on the interior surface of the internal cooling cavity, wherein the plurality of trip strips and the at least one separating feature of the interior surface are spaced from the exterior surface of the baffle insert.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: September 24, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Atul Kohli
  • Dual cavity baffle
    Patent number: 10415428
    Abstract: A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.
    Type: Grant
    Filed: January 31, 2018
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Corey D. Anderson
  • Modified structural truss for airfoils
    Patent number: 10378364
    Abstract: An airfoil for use with a gas turbine engine includes a pressure side wall. The airfoil further includes a suction side wall configured to be exposed to less pressure than the pressure side wall during operation of the gas turbine engine. The airfoil also includes a plurality of ribs defining multiple air passages including at least one triangular air passage partially defined by at least one of the pressure side wall or the suction side wall, and at least one internal air passage bordered on at least three sides by at least two of the plurality of ribs.
    Type: Grant
    Filed: November 7, 2017
    Date of Patent: August 13, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Edwin Otero, David R. Pack
  • HEAT TRANSFER AUGMENTATION FEATURE FOR COMPONENTS OF GAS TURBINE ENGINES
    Publication number: 20190242270
    Abstract: Components for gas turbine engines are provided. The components include a component body having a hot side and a cold side, an attachment element extending from the cold side of the component body, a component extension extending from the component body at the attachment element to an end surface, the component extension having a cold-side first portion and a cold-side second portion, wherein the cold-side first portion is a portion of the component extension between the attachment element and the cold-side second portion, and the cold-side second portion is a portion of the component extension extending from the cold-side first portion to the end surface of the component extension, and a cold-side heat transfer augmentation feature on the cold-side second portion of the component extension, wherein the cold-side first portion defines a uniform surface.
    Type: Application
    Filed: February 5, 2018
    Publication date: August 8, 2019
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • DUAL CAVITY BAFFLE
    Publication number: 20190234236
    Abstract: A component for a gas turbine engine according to example of the present disclosure includes a body that has an airfoil extending between a radially inner platform and a radially outer platform, and that has an internal cavity within the airfoil. A baffle is disposed within the internal cavity. The baffle defines first and second baffle cavities that are separated by a baffle dividing wall extending between the radially inner platform and the radially outer platform. An impingement plate is spaced apart from one of the radially inner and outer platforms, includes a first opening that provides fluid communication between a first chamber and the first baffle cavity, and includes a plurality of second openings that are smaller than the first opening and provide fluid communication between the first chamber and the second baffle cavity via a second chamber.
    Type: Application
    Filed: January 31, 2018
    Publication date: August 1, 2019
    Inventors: Brandon W. Spangler, Corey D. Anderson
  • VANE FLOW DIVERTER
    Publication number: 20190234235
    Abstract: A vane section of a gas turbine engine according to an example of the present disclosure includes a platform and an airfoil extending outwardly from the platform and having an internal channel communicating with an opening in the platform. A rail extends inwardly from the platform, such that a surface of the platform opposite the airfoil and the rail at least partially define a platform cavity. A flow diverter extends inwardly of the platform within the platform cavity and defines a diverter cavity, an inlet configured to receive fluid flowing in a first direction from the opening in the platform to the diverter cavity, and an outlet configured to expel fluid from the diverter cavity to the platform cavity in a second direction different from the first direction.
    Type: Application
    Filed: January 31, 2018
    Publication date: August 1, 2019
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • PLATFORM LIP IMPINGEMENT FEATURES
    Publication number: 20190234234
    Abstract: An exemplary gas turbine engine includes a turbine section positioned about an engine central longitudinal axis. The turbine section includes a component with a platform providing a lip, a rail extending radially from the platform and at an axial location spaced from an outer axial extension of the lip. An inner face of the rail and a surface of the platform at least partially provide a cavity. At least one opening extends from the inner face to an outer face of the rail opposite the inner face to provide fluid communication from the cavity to the lip.
    Type: Application
    Filed: January 31, 2018
    Publication date: August 1, 2019
    Inventors: Corey D. Anderson, Brandon W. Spangler
  • Gas turbine engine component having platform trench
    Patent number: 10364680
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge and circumferentially extends between a first mate face and a second mate face and a trench disposed on at least one of the first mate face and the second mate face. A plurality of cooling holes are axially disposed within the trench.
    Type: Grant
    Filed: August 14, 2012
    Date of Patent: July 30, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Bret M. Teller, Mark F. Zelesky, Scott D. Lewis, Brandon W. Spangler, Ricardo Trindade
  • GAS TURBINE ENGINE COMPONENT COOLING WITH RESUPPLY OF COOLING PASSAGE
    Publication number: 20190226345
    Abstract: A gas turbine engine component with a core includes a first core portion configured to provide a first cooling passage. A second core portion is spaced from the first core portion and configured to provide a second cooling passage. The second core portion includes a longitudinal leg and a resupply leg transverse to and intersecting the longitudinal leg. The resupply leg has a terminal end and is configured to provide a resupply channel A connector interconnects the terminal end to the first core portion. The connector is configured to provide a resupply hole.
    Type: Application
    Filed: April 1, 2019
    Publication date: July 25, 2019
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, JR.
  • Gas turbine engine component having shaped pedestals
    Patent number: 10358978
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of C-shaped pedestals and a second set of C-shaped pedestals adjacent to the first set of C-shaped pedestals.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: July 23, 2019
    Assignee: United Technologies Corporation
    Inventors: Dominic J. Mongillo, Brandon W. Spangler
  • Manufacturing method for a dual wall component
    Patent number: 10352172
    Abstract: A dual wall component includes a first outer wall extending from a leading edge to a trailing edge, a first inner wall spaced from the first outer wall by a plurality of first cavities and first ribs, a second inner wall spaced from the first inner wall by a plurality of second cavities and second ribs, and a second outer wall extending from the leading edge to the trailing edge and spaced from the second inner wall by a plurality of third cavities and third ribs. Portions of the first and second outer walls have thicknesses less than about 0.018? (0.457 mm). In a method for forming a dual wall component, component walls are formed by additive manufacturing and without using cores to form the cavities.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: July 16, 2019
    Assignee: United Technologies Corporation
    Inventor: Brandon W. Spangler
  • Gas turbine engine component with a baffle insert
    Patent number: 10337334
    Abstract: A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface of the baffle insert, wherein the plurality of trip strips and the at least one rib are spaced from an interior surface of the internal cooling cavity.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: July 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Atul Kohli
  • Baffle inserts
    Patent number: 10329932
    Abstract: An airfoil includes an airfoil body extending from an inner diameter platform to an opposed outer diameter platform along a longitudinal axis. The airfoil body defines a leading edge and a trailing edge and has a cavity defined between the leading edge, the trailing edge, the inner diameter platform and the outer diameter platform. The cavity includes an airfoil protrusion extending inward from an inner surface of the airfoil body. The airfoil includes a baffle body within the cavity extending along a baffle body axis. The baffle body has a baffle protrusion extending along a central protrusion axis at an angle with respect to the baffle body axis. The end of the baffle protrusion abuts an end of the airfoil protrusion. A flow path is defined between the inner surface of the airfoil body and the outer surface of the baffle body.
    Type: Grant
    Filed: March 2, 2015
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Gina Cavallo
  • Flapper seal apparatus and system
    Patent number: 10329933
    Abstract: An engine component for isolating a first pressure and/or first flow and a second pressure and/or second flow is provided. The engine component may comprise a body portion, a first seal element and a second seal element. The body portion may include a first standoff and a second standoff. The first seal element housed within the body portion. The second seal element may also be housed within the body portion. The second seal element may be coupled to the first seal element.
    Type: Grant
    Filed: March 17, 2015
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Richard N. Allen, Brandon W. Spangler