Patents by Inventor Thomas N. Slavens

Thomas N. Slavens 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).

  • Method for providing coolant to a movable airfoil
    Patent number: 10385720
    Abstract: A gas turbine engine with an adjustable vane includes a platform with a hole and an aperture. A vane is supported for rotation relative to the platform by a trunion that is received in the hole. The vane has an opening that is laterally spaced from the trunion and is in alignment with the aperture. The vane includes an airfoil with a cooling passage in fluid communication with the opening.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: John D. Teixeira, Thomas N. Slavens, Raymond Surace
  • Airfoil contour for low-loss on-boarding of cooling air through an articulating spindle
    Patent number: 10385728
    Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Eric A. Grover, John D. Teixeira
  • Gas turbine engine component cooling circuit with respirating pedestal
    Patent number: 10370981
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a pedestal that traverses a flow channel disposed between a first wall and a second wall. The pedestal includes at least one interior bore configured to communicate a cooling fluid inside of the pedestal.
    Type: Grant
    Filed: January 26, 2015
    Date of Patent: August 6, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Brooks E. Snyder
  • Twin centrifugal single spool engine
    Patent number: 10364041
    Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.
    Type: Grant
    Filed: July 25, 2016
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Arthur W. Utay, Tania Bhatia Kashyap, Thomas N. Slavens, Kevin L. Rugg, Mark F. Zelesky, Brian D. Merry, Gabriel L. Suciu
  • Gas turbine engine component cooling passage turbulator
    Patent number: 10364683
    Abstract: A gas turbine engine component includes opposing walls that provide an interior cooling passage. One of the walls has a turbulator with a hook that is enclosed within the walls.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: July 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Brooks E. Snyder, Thomas N. Slavens, Nicholas M. LoRicco, James T. Auxier
  • CENTRIFUGAL AIRFOIL COOLING MODULATION
    Publication number: 20190211691
    Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
    Type: Application
    Filed: March 14, 2019
    Publication date: July 11, 2019
    Inventors: Lane Thornton, Thomas N. Slavens
  • Cupped contour for gas turbine engine blade assembly
    Patent number: 10344597
    Abstract: An exemplary method of forming an endwall with a contour includes casting an endwall with at least one cooling channel having an opening from the endwall, and covering the opening with a cupped contour formed on the endwall. An exemplary gas turbine engine blade assembly includes an endwall with a plurality of cooling channels, an airfoil extending radially from the endwall to a tip, and a cupped contour formed on the endwall to provide a cooling chamber between the cupped contour and a radially facing surface of the endwall.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dipanjan Saha, Brooks E. Snyder, Thomas N. Slavens
  • Gas turbine engine airfoil leading edge cooling
    Patent number: 10329923
    Abstract: An example gas turbine engine component includes an airfoil having a leading edge area, a first circuit to cool a first section of the leading edge area, and a second circuit to cool a second section of the leading edge area. The first circuit separate and distinct from the second circuit within the airfoil.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Dominic J. Mongillo, Jr., Matthew A. Devore
  • Multiple piece engine component
    Patent number: 10329918
    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine, including a component having a first portion formed using one of a casting and a forging process, and a second portion formed using an additive manufacturing process.
    Type: Grant
    Filed: October 17, 2014
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Mark F. Zelesky
  • Cooling configuration for a component
    Patent number: 10329921
    Abstract: A component includes at least one thermal riser that extends from an exterior surface of the component. At least one cooling passage extends through a wall and adjoins an interior cooling passage and provides an exterior surface. At least one cooling passage is configured to direct cooling fluid through the wall adjacent to at least one thermocouple.
    Type: Grant
    Filed: October 8, 2015
    Date of Patent: June 25, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Carey Clum
  • GAS TURBINE ENGINE COMPONENT COOLING PASSAGE AND SPACE EATING CORE
    Publication number: 20190176228
    Abstract: A gas turbine engine includes a structure that has walls that provide a cooling passage and a cooling surface. A non-ferrous obstruction is relative to the walls. The obstruction includes a portion spaced from the cooling surface to provide a gap which is configured to receive a cooling fluid.
    Type: Application
    Filed: February 14, 2019
    Publication date: June 13, 2019
    Inventors: Thomas N. Slavens, Lane Thornton, Sasha M. Moore, Nicholas M. LoRicco
  • Gas turbine engine component having curved turbulator
    Patent number: 10316668
    Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a wall that forms a portion of an outer periphery of at least one cavity and at least one curved turbulator that extends from said wall.
    Type: Grant
    Filed: January 31, 2014
    Date of Patent: June 11, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mosheshe Camara-Khary Blake, Lisa K. Osborne, Thomas N. Slavens
  • Additively manufactured casting articles for manufacturing gas turbine engine parts
    Patent number: 10307817
    Abstract: A casting article according to another exemplary aspect of the present disclosure includes, among other things, a circuit forming portion including an interior channel and an outer shell body that surrounds the interior channel. An engineered failure feature is formed in the outer shell body and is configured to increase compressibility of the casting article during a casting process.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: June 4, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Mark F. Zelesky, JinQuan Xu, Joel H. Wagner
  • Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component
    Patent number: 10307816
    Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.
    Type: Grant
    Filed: October 26, 2015
    Date of Patent: June 4, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N Slavens, James Tilsley Auxier
  • Incident tolerant turbine vane gap flow discouragement
    Patent number: 10301967
    Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.
    Type: Grant
    Filed: October 17, 2014
    Date of Patent: May 28, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Steven Bruce Gautschi
  • Incident tolerant turbine vane cooling
    Patent number: 10287900
    Abstract: A disclosed turbine vane assembly for a gas turbine engine includes an airfoil including a pressure side and a suction side that extends from a leading edge toward a trailing edge. The airfoil is rotatable about an axis transverse to an engine longitudinal axis and includes a forward chamber within the airfoil and in communication with a cooling air source, a forward impingement baffle defining a pre-impingement cavity within the forward chamber. The pre-impingement cavity is split into a leading edge cavity, pressure side cavity and a suction side cavity defined between an inner surface of the forward chamber and an outer surface of the forward impingement baffle.
    Type: Grant
    Filed: October 17, 2014
    Date of Patent: May 14, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Matthew A. Devore
  • Centrifugal airfoil cooling modulation
    Patent number: 10273809
    Abstract: In one example embodiment, a blade includes an attachment region, an airfoil extending from the attachment region, and a blade cooling arrangement. The blade cooling arrangement includes at least a first feed passage disposed through the attachment region, which is connected to a first cooling passage disposed in the airfoil. A passively actuated first coolant valve is disposed in or proximate the first feed passage. A plurality of such blades can be disposed in a turbine section of an engine.
    Type: Grant
    Filed: December 8, 2014
    Date of Patent: April 30, 2019
    Assignee: United Technologies Corporation
    Inventors: Lane Thornton, Thomas N. Slavens
  • ADDITIVELY MANUFACTURED CORE FOR USE IN CASTING AN INTERNAL COOLING CIRCUIT OF A GAS TURBINE ENGINE COMPONENT
    Publication number: 20190118245
    Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes a base core portion and an additive core portion additively manufactured to the base core portion. A method of manufacturing a core for use in casting an internal cooling circuit within a gas turbine engine component including additively manufacturing an additive core portion to a base core portion.
    Type: Application
    Filed: December 12, 2018
    Publication date: April 25, 2019
    Applicant: United Technologies Corporation
    Inventors: Thomas N. Slavens, James Tilsley Auxier
  • System and Process to Provide Self-Supporting Additive Manufactured Ceramic Core
    Publication number: 20190111471
    Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component, the core including a core body with an outer skin in which a core body additively manufacturing binder is locally eliminated. A method of manufacturing a core for casting a component, including casting a core body for at least partially forming an internal passage architecture of a component; and forming an outer skin on the core body in which a core body binder is locally eliminated.
    Type: Application
    Filed: December 10, 2018
    Publication date: April 18, 2019
    Applicant: United Technologies Corporation
    Inventors: Thomas N. Slavens, James T. Auxier
  • Gas turbine engine component cooling passage and space casting core
    Patent number: 10259039
    Abstract: A method of manufacturing a component that includes providing a core structure, casting a component about the core structure, removing a first portion of the core structure from the cast component, and leaving a second portion of the core structure in the cast component to provide a reduced cross-section in the cast component.
    Type: Grant
    Filed: January 16, 2014
    Date of Patent: April 16, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Lane Thornton, Sasha M. Moore, Nicholas M. LoRicco