Patents Examined by Craig Kim
  • Patent number: 10260419
    Abstract: A thermal management system for a gas turbine engine and/or an aircraft is provided including a thermal transport bus having a heat exchange fluid flowing therethrough. The thermal management system also includes a plurality of heat source exchangers and at least one heat sink exchanger. The plurality of heat source exchangers and the at least one heat sink exchanger are in thermal communication with the heat exchange fluid in the thermal transport bus. The plurality of heat source exchangers are arranged along the thermal transport bus and configured to transfer heat from one or more accessory systems to the heat exchange fluid, and the at least one heat sink exchanger is located downstream of the plurality of heat source exchangers and configured to remove heat from the heat exchange fluid.
    Type: Grant
    Filed: July 31, 2015
    Date of Patent: April 16, 2019
    Assignee: General Electric Company
    Inventors: Matthew Robert Cerny, Christopher James Kroger, Brandon Wayne Miller
  • Patent number: 10247096
    Abstract: An inlet cooling system unit that is fluidly coupled to a gas turbine can include a filter module configured to filter inlet air, a chiller module configured to cool inlet air, and a framework. The framework is sized and shaped to define a filer module receiving region which supportably receives the filter module, and a chiller module receiving region which supportably receives the chiller module, the chiller module receiving region located below the filter module receiving region such that the chiller module is received below the filter module. Related gas turbine inlet cooling systems are also provided.
    Type: Grant
    Filed: February 21, 2018
    Date of Patent: April 2, 2019
    Assignee: S&T Mfg. Co.
    Inventors: Ian Spanswick, Gary Hilberg
  • Patent number: 10247102
    Abstract: A single, unitary fuel/oil manifold for a gas turbine engine is provided which comprises one or more interfaces for mounting various fuel system and lubricating system components directly to the fuel/oil manifold. The fuel/oil manifold also defines fluid passages for transferring fuel or lubricant from one component to another component. Packing numerous fuel system and lubricating system components within the fuel/oil manifold reduces cost and weight and simplifies maintenance.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: April 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael Dreher, Ryan K. Snyder, James M. McPherson, Ping Su, Fernando Quinones, Gabriel Rivera
  • Patent number: 10247017
    Abstract: A system includes a gas delivery disk coupled to a second shaft, wherein the second shaft and the gas delivery disk are disposed about an axis. The gas delivery disk includes an inner axial opening configured to facilitate a first axial flow through a first passage within the second shaft, a duct configured to supply a bearing flow in a radial direction toward the axis, and a bearing face disposed within the first passage and radially interior to the inner axial opening. The bearing face is configured to receive the bearing flow, and the bearing face is configured to form a gas bearing between the bearing face and a first shaft disposed about the axis.
    Type: Grant
    Filed: June 29, 2016
    Date of Patent: April 2, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Brandon Wayne Miller, Thomas Lee Becker, Daniel Alan Niergarth, Bugra Han Ertas
  • Patent number: 10240793
    Abstract: A manifold fitting receiving radial and axial manifolds and providing two radial outlets is disclosed. The manifold fitting, when used in conjunction with a fuel injector and a combustor for a gas turbine engine, reduces the radial footprint of the fuel injector and thereby allows for a more compact engine. Additionally, the manifold fitting eliminates parts, reducing weight in the process, as compared to prior art fittings. Such reductions in size, parts count, and weight are particularly beneficial for aircraft applications.
    Type: Grant
    Filed: April 22, 2014
    Date of Patent: March 26, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Kevin Joseph Low
  • Patent number: 10244614
    Abstract: Two ceramic or sapphire pieces are welded together using a plasma torch that includes a cylindrical vessel having first and second ends, a tangential inlet connected to or proximate to the first end, a tangential outlet connected to or proximate to the second end, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is aligned with a longitudinal axis of the cylindrical vessel, and extends into the cylindrical vessel. A hollow electrode nozzle is connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel. A second electrode is positioned proximate to the hollow electrode nozzle. The two ceramic or sapphire pieces are placed between the second electrode and the hollow electrode, and are welded together with the plasma exiting from the hollow electrode.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: March 26, 2019
    Assignee: FORET PLASMA LABS, LLC
    Inventor: Todd Foret
  • Patent number: 10228135
    Abstract: The present disclosure is directed to a combustor including an annularly shaped liner that at least partially defines a hot gas path of the combustor and a flow sleeve that circumferentially surrounds at least a portion of the liner. The flow sleeve is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies circumferentially spaced about the flow sleeve and each fuel injector assembly extends radially through the flow sleeve, the cooling flow annulus and the liner. A first portion of the flow sleeve defined between a first pair of circumferentially adjacent fuel injector assemblies of the plurality of fuel injector assemblies bulges radially outwardly with respect to an outer surface of the liner so as to enlarge a flow volume of the cooling flow annulus.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Ronnie Ray Pentecost, Jonathan Hale Kegley
  • Patent number: 10227928
    Abstract: A gas turbine engine comprises a fan, a compressor, a turbine having first stage blades and second stage blades, the first stage blades rotates in a first direction and the second stage blades rotates in a second direction opposite the first direction. The first stage blades are directly adjacent to one another, a drive in operable input connection with the fan and in operable output connection with the first stage blades and the second stage blades, the first stage blades and the second stage blades driving the fan through the drive.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Craig Miller Kuhne, Christopher Charles Glynn, Randy M. Vondrell, Andrew Breeze-Stringfellow, Kurt David Murrow, Darek T. Zatorski, Donald Scott Yeager, Nicholas Rowe Dinsmore, Samuel Jacob Martin, Donald Albert Bradley
  • Patent number: 10220474
    Abstract: A method of making a combustor cap assembly uses an additive manufacturing process of consecutively adding material in layers along an upstream axial build direction starting from a base side positioned transverse to the upstream axial build direction. The base side has at least one acoustic port. A bump side extends from the base side in the upstream axial build direction and has at least one damper projecting from the bump side. The damper has at least one inclined face forming an angle with the upstream axial build direction of less than or equal to 45 degrees. The resulting cap assembly includes a hot side with an acoustic port and a cold side with at least one damper with an inclined face and a damper chamber in communication with the acoustic port.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: March 5, 2019
    Assignee: General Electricd Company
    Inventors: Andre Theuer, Dariusz Oliwiusz Palys, Jost Imfeld
  • Patent number: 10215039
    Abstract: A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.
    Type: Grant
    Filed: July 12, 2016
    Date of Patent: February 26, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventor: Anthony L. Schiavo
  • Patent number: 10215027
    Abstract: An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body with a weld at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. A method of constructing an airfoil is also disclosed as is a gas turbine engine.
    Type: Grant
    Filed: October 7, 2015
    Date of Patent: February 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Michael A. Weisse
  • Patent number: 10208676
    Abstract: Axially adjacent annular booster bleed aft and forward plenums with annular common wall therebetween extend radially outwardly from transition duct. Variable bleed valve includes bleed valve door in bleed inlet in transition duct, attached to rotatable valve body rotatable about axis of rotation, operable to open and close bleed inlet to aft plenum. Rotatable plenum door clocked or circumferentially spaced apart from variable bleed valve door and attached to rotatable valve body, operable to close and open up and control flow through an inter plenum aperture in common wall. Aft and forward bleed exhaust ducts extend from booster bleed aft and forward plenums to bypass flow path. One or more heat exchanger, such as from thermal management system, may be disposed in the bleed exhaust ducts. Heat exchangers may be used for cooling oil for power gear box and/or engine bearings, air conditioning, or variable frequency generator.
    Type: Grant
    Filed: March 29, 2016
    Date of Patent: February 19, 2019
    Assignee: General Electric Company
    Inventors: Steven Douglas Johnson, Brandon Wayne Miller, Craig Alan Gonyou
  • Patent number: 10208621
    Abstract: A surface cooler includes a base component, a plurality of first fins, and a plurality of second fins. The base component has a first surface, a second surface, and a first thermally conductive material. The plurality of first fins extends substantially perpendicular from the first surface and each first fin is characterized by a first height and a first width. The plurality of second fins extends substantially perpendicular from the first surface and each second fin is characterized by a second height and a second width. One or more fins of the plurality of first fins are disposed between a pair of adjacent fins of the plurality of second fins and an average first height of the plurality of first fins is lower than an average second height of the plurality of second fins. The plurality of fins reduces air drag and augments heat transfer capacity of surface cooler.
    Type: Grant
    Filed: December 7, 2015
    Date of Patent: February 19, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Florian Hoefler, Carlos Enrique Diaz, Jorge Alejandro Carretero Benignos
  • Patent number: 10197278
    Abstract: A combustor assembly for a gas turbine engine is provided. The combustor assembly includes a liner at least partially defining a combustion chamber and extending between an aft end a forward end generally along an axial direction. The combustor assembly also includes an annular dome including an enclosed surface defining a slot for receipt of the forward end of the liner. A cap is positioned at the forward end of the liner and at least partially positioned within the slot defined by the enclosed surface of the annular dome. The cap includes a surface configured to contact at least one of the enclosed surface of the annular dome and the forward end of the liner. Such a configuration may form a substantially airtight seal between the forward end of the liner and the annular dome despite a relative thermal expansion between the components.
    Type: Grant
    Filed: September 2, 2015
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Nicholas John Bloom, Daniel Kirtley, Michael Alan Stieg, Brian Christopher Towle, Chad Holden Sutton
  • Patent number: 10196986
    Abstract: In one aspect, the present disclosure is directed to a bearing compartment sealing system including a bearing for supporting a shaft. A housing encloses the bearing and defines a compartment for holding lubricant therein. At least two seals are located between the shaft and the housing. The at least two seals, the housing, and the shaft collectively enclose the compartment. Only one of the at least two seals is a hydrodynamic seal.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: February 5, 2019
    Assignee: General Electric Company
    Inventors: Ning Fang, Scott Wolfer, Adam Mitchell Record, Jonathan K. Remer, Daryl Scott Schneider, Jacob Patrick Miller, Kyle Robert Snow
  • Patent number: 10184665
    Abstract: A fuel nozzle is provided for a gas turbine engine, and can include a pilot fuel injector having an axially-elongated, inner pilot centerbody wall and an outer pilot centerbody wall, with the axially-elongated, inner pilot centerbody wall extending from an upstream end to an annular fuel passage defining the downstream end of the pilot fuel injector. The fuel passage intersects with the inner pilot centerbody wall at a pilot fuel metering orifice. The fuel nozzle also includes a pilot fuel film surface downstream from the annular fuel passage and an annular splitter surrounding the pilot fuel injector. The annular splitter comprises, in axial sequence: an upstream section, a splitter throat having a diameter that is larger than a downstream diameter defined by the pilot fuel film surface, and a downstream diverging surface having an average diverging angle of about 24° to about 40° in relation to a centerline axis.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: January 22, 2019
    Assignee: General Electric Company
    Inventors: Michael Anthony Benjamin, Alfred Albert Mancini, Rameshkumar Muthuvel Chandrasekaran
  • Patent number: 10184402
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.
    Type: Grant
    Filed: April 9, 2018
    Date of Patent: January 22, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry
  • Patent number: 10184425
    Abstract: A control system for a variable area fan nozzle (VAFN) having a plurality of petals is disclosed. The control system may include at least one fiber optic shape sensor extending along at least one of the plurality of petals, and a light source operatively connected to the at least one fiber optic shape sensor. The control system may further include a receiver operatively connected to the at least one fiber optic shape sensor. The control system may further include a VAFN control unit in operative communication with the plurality of petals and the receiver. The VAFN control unit may be configured to receive a signal from the receiver indicative of the measured strain along the at least one fiber optic shape sensor, and calculate a nozzle area of the VAFN based on the measured strain.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: January 22, 2019
    Assignee: The Boeing Company
    Inventors: Jason J. Jackowski, Kent E. Karnofski
  • Patent number: 10174949
    Abstract: A heat shield for a combustor of a gas turbine engine includes a first edge with a first set of cantilevered members and a second edge with a second set of cantilevered members.
    Type: Grant
    Filed: February 5, 2014
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Frank J. Cunha, Nurhak Erbas-Sen
  • Patent number: 10174682
    Abstract: Provided are more efficient techniques for operating gas turbine systems. In one embodiment a gas turbine system comprises an oxidant system, a fuel system, a control system, and a number of combustors adapted to receive and combust an oxidant from the oxidant system and a fuel from the fuel system to produce an exhaust gas. The gas turbine system also includes a number of oxidant-flow adjustment devices, each of which are operatively associated with one of the combustors, wherein an oxidant-flow adjustment device is configured to independently regulate an oxidant flow rate into the associated combustor. An exhaust sensor is in communication with the control system. The exhaust sensor is adapted to measure at least one parameter of the exhaust gas, and the control system is configured to independently adjust each of the oxidant-flow adjustment devices based, at least in part, on the parameter measured by the exhaust sensor.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: January 8, 2019
    Assignee: ExxonMobil Upstream Research Company
    Inventors: Franklin F. Mittricker, Richard A. Huntington