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).

  • Heat temperature gradient heat exchanger
    Patent number: 10260422
    Abstract: A heat exchanger assembly includes an outer manifold defining an outer cavity. An inner cavity is defined by an inner shell supported within the outer manifold and at least partially surrounded by the outer cavity. The inner shell includes a plurality of impingement openings for directing airflow into the inner cavity. An inner manifold is supported within the inner cavity. The inner manifold is exposed to impingement airflow through the plurality of impingement openings in the inner shell. The inner manifold includes a plurality of flow passages and at least one insulator pocket substantially aligned with the plurality of flow passages. A cooled cooling air system for a gas turbine engine and a gas turbine engine assembly are also disclosed.
    Type: Grant
    Filed: May 6, 2016
    Date of Patent: April 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Mosheshe Camara-Khary Blake
  • Low modulus shot sleeve for high temperature die casting
    Patent number: 10245637
    Abstract: Shot sleeves for high temperature die casting include a nickel-based alloy having a low modulus single crystal with axi-symmetric orientation.
    Type: Grant
    Filed: August 26, 2016
    Date of Patent: April 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: John Joseph Marcin, Dilip M. Shah, Carl R. Verner, Albert Rabinovich, Weiduo Yu, Thomas N. Slavens
  • Gas turbine engine component with increased cooling capacity
    Patent number: 10247011
    Abstract: A cooling circuit for a gas turbine engine comprises a gas turbine engine component having a body with at least one internal cavity defined by a cavity wall. A plurality of cooling holes formed within the cavity wall, wherein each cooling hole is defined by a length extending from a cooling hole inlet to a cooling hole outlet, and wherein the cooling holes are positioned relative to each other such that a minimum allowable ligament distance is maintained between adjacent cooling holes along the entire length of each cooling hole. A gas turbine engine and a method of forming a cooling circuit for a gas turbine engine are also disclosed.
    Type: Grant
    Filed: October 27, 2015
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: San Quach, Christopher King, Thomas N. Slavens
  • Pedestals with heat transfer augmenter
    Patent number: 10247099
    Abstract: A gas turbine engine component comprises a first side wall, and a second side wall spaced apart from the first side wall. At least one internal cooling channel is formed between the first and second side walls. At least one pedestal is positioned within the at least one cooling channel and has a body extending from a first end connected to the first side wall to a second end connected to the second side wall. The body includes at least one protrusion.
    Type: Grant
    Filed: October 16, 2014
    Date of Patent: April 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Thomas N. Slavens
  • Combustor liner panel with a multiple of heat transfer ribs for a gas turbine engine combustor
    Patent number: 10247419
    Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
    Type: Grant
    Filed: August 1, 2017
    Date of Patent: April 2, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Mark F. Zelesky, Andrew D. Burdick
  • Gas turbine engine airfoil with leading edge trench and impingement cooling
    Patent number: 10240464
    Abstract: A gas turbine engine airfoil includes an airfoil structure including an exterior surface that is provided by an exterior wall that has a leading edge. A radially extending interior wall within the airfoil structure separates first and second radial cooling passages. The first cooling passage is arranged near the leading edge. A radially extending trench is in the leading edge. An impingement hole is provided in the interior wall and is configured to direct a cooling fluid from the second cooling passage to the first cooling passage and onto the exterior wall at the leading edge.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: March 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Brooks E. Snyder
  • ANTI-DEFLECTION FEATURE FOR ADDITIVELY MANUFACTURED THIN METAL PARTS AND METHOD OF ADDITIVELY MANUFACTURING THIN METAL PARTS
    Publication number: 20190085719
    Abstract: A conduction riser is additively manufactured onto thin metal parts, the conduction riser extends in a build direction of the thin metal part and traverses a surface of the thin metal part as the conduction riser extends in the build direction. The conduction riser transfers heat from the upper layers of the additively manufactured part during manufacturing to prevent thermal deflection of the part during the manufacturing process.
    Type: Application
    Filed: September 7, 2018
    Publication date: March 21, 2019
    Inventors: Thomas N. Slavens, Brooks E. Snyder
  • Tangential on-board injectors for gas turbine engines
    Patent number: 10233842
    Abstract: A tangential on-board injector (TOBI) for a gas turbine engine and methods of making the same are provided. The TOBI includes at least one adjustable strut configured to control an airflow through the TOBI, the at least one adjustable strut moveable to change an airflow characteristic within the TOBI.
    Type: Grant
    Filed: January 8, 2016
    Date of Patent: March 19, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Carey Clum, Thomas N. Slavens
  • Additively manufactured core for use in casting an internal cooling circuit of a gas turbine engine component
    Patent number: 10226812
    Abstract: A core for use in casting an internal cooling circuit within a gas turbine engine component includes an additively manufactured skeleton core portion manufactured of a refractory metal, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material, a surround core portion that at least partially encapsulates the additively manufactured skeleton core portion, the surround core portion manufactured of a ceramic material and a cooling hole shape that extends from the additively manufactured skeleton core portion through the surround core portion, the cooling hole shape operable to form a cooling hole.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: March 12, 2019
    Assignee: United Technologies Corporation
    Inventors: James Tilsley Auxier, Thomas N Slavens
  • Cooling features with three dimensional chevron geometry
    Patent number: 10208604
    Abstract: An internally cooled component of a gas turbine engine is provided. The component may include a cooling passage at least partially defined by a first wall and a second wall with a first pedestal extending from the first wall to the second wall. The first pedestal may have a chevron geometry. A second pedestal may extend from the first wall to the second wall and also have a chevron geometry. A gap may be defined by the first pedestal and the second pedestal with the gap oriented between the first pedestal and the second pedestal.
    Type: Grant
    Filed: April 27, 2016
    Date of Patent: February 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Brooks E. Snyder
  • COMBUSTOR LINER PANEL WITH A MULTIPLE OF HEAT TRANSFER RIBS FOR A GAS TURBINE ENGINE COMBUSTOR
    Publication number: 20190041059
    Abstract: A liner panel for use in a combustor of a gas turbine engine, including a multiple of heat transfer ribs located in at least one discrete area of the liner panel. A wall assembly within a gas turbine engine including a support shell, a liner panel mounted to the support shell via a multiple of studs and a multiple of heat transfer ribs located in at least one discrete area on a cold side of the liner panel, each of the multiple of heat transfer ribs account for the multiple of studs.
    Type: Application
    Filed: August 1, 2017
    Publication date: February 7, 2019
    Applicant: United Technologies Corporation
    Inventors: Thomas N. Slavens, Mark F. Zelesky, Andrew D. Burdick
  • GAS TURBINE ENGINE COOLING ARRANGEMENT
    Publication number: 20190040796
    Abstract: A gas turbine engine cooling arrangement includes a component and a pedestal. The component of a gas turbine engine has a first surface and a second surface disposed opposite the first surface. The pedestal is disposed on the second surface. The pedestal has an outer surface extending along a first axis away from the second surface between a pedestal base and a pedestal top. A first lobe is defined by the outer surface and extends along an axis that is disposed parallel to the first axis.
    Type: Application
    Filed: August 3, 2017
    Publication date: February 7, 2019
    Inventors: Thomas N. Slavens, Andrew D. Burdick
  • Cooling for gas turbine engine components
    Patent number: 10196902
    Abstract: A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.
    Type: Grant
    Filed: September 15, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sasha M. Moore, Timothy J. Jennings, Thomas N. Slavens, Clifford J. Musto, Nicholas M. LoRicco, Carey Clum, John McBrien, Christopher Whitfield, San Quach
  • Conduit cooling system and method of supplying cooling fluid to a conduit
    Patent number: 10196924
    Abstract: A conduit system for a gas turbine engine includes, a heat exchanger configured to cool fluid flowing therethrough having an inlet and an outlet, at least one by-pass in operable communication with the heat exchanger that is configured to allow fluid to exit the heat exchanger before reaching the outlet, and a conduit that is in fluidic communication with the outlet and the at least one by-pass.
    Type: Grant
    Filed: August 17, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Carey Clum
  • Method and system for controlling coating in non-line-of-sight locations
    Patent number: 10179948
    Abstract: A method for coating a turbine engine component, said method includes the steps of: placing the component into a chamber; injecting a non-reactive carrier gas containing a coating material into the chamber; and forming a coating on a desired portion of the component by locally heating the desired portion of the component by redirecting a directed energy beam onto the desired portion of the component.
    Type: Grant
    Filed: April 17, 2015
    Date of Patent: January 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Brooks E Snyder, Thomas J Martin, Thomas N Slavens
  • System and process to provide self-supporting additive manufactured ceramic core
    Patent number: 10179362
    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: Grant
    Filed: July 20, 2016
    Date of Patent: January 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N Slavens, James T Auxier
  • Highly cooled die casting plunger
    Patent number: 10173261
    Abstract: A die casting plunger tip includes a hollow outer portion and a hollow inner portion. The outer portion has a first closed end. The inner portion has a second partially closed end. The inner portion is disposed within the outer portion and the second partially closed end is adjacent the first closed end of the outer portion in an axial direction. A plurality of connectors connects the outer portion and the inner portion. A plenum is formed between the outer portion and the inner portion.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Carl R. Verner, Albert Rabinovich, Weiduo Yu, Awadh B. Pandey
  • Die cast tip cover and method of managing radial deflection of die cast tip
    Patent number: 10166601
    Abstract: A die casting plunger tip assembly includes a first portion having a closed end defining an outer face and a tip cover disposed on the outer face of the closed end. The tip cover includes a support structure extending from an inner surface of the tip cover toward the closed end. The support structure is positioned in contact with the outer face of the closed end and a cavity is formed between the outer face of the closed end and the tip cover.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: January 1, 2019
    Assignee: United Technologies Corporation
    Inventors: Thomas N. Slavens, Nicholas M LoRicco
  • FLUIDIC MACHINING METHOD AND SYSTEM
    Publication number: 20180363473
    Abstract: One exemplary embodiment of this disclosure relates to a method of forming an engine component. The method includes forming an engine component having an internal passageway, the internal passageway formed with an initial dimension. The method further includes establishing a flow of machining fluid within the internal passageway, the machining fluid changing the initial dimension.
    Type: Application
    Filed: August 10, 2018
    Publication date: December 20, 2018
    Inventors: Sasha M. Moore, Thomas N. Slavens, Nicholas M. Loricco, Timothy J. Jennings
  • Gas turbine engine component having vascular engineered lattice structure
    Patent number: 10156359
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: December 18, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark F. Zelesky, Joel H. Wagner, Tracy A. Propheter-Hinckley, Michael F. Blair, Thomas N. Slavens, Dominic J. Mongillo