Patents Examined by Craig Kim
  • Patent number: 10113747
    Abstract: The present disclosure generally relates to a system with a gas turbine engine. The gas turbine engine includes a first combustor having a first fuel injector and a second combustor having a second fuel injector. The gas turbine engine further includes a first fuel conduit extending from a first orifice to a first fuel outlet of the first fuel injector. The first fuel conduit has a first acoustic volume between the first orifice and the first fuel outlet. The gas turbine engine further includes a second fuel conduit extending from a second orifice to a second fuel outlet of the second fuel injector. The second fuel conduit has a second acoustic volume between the second orifice and the second fuel outlet, and the first acoustic volume and the second acoustic volume are different from one another.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: October 30, 2018
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Hasan Karim, Joel Meador Hall
  • Patent number: 10113484
    Abstract: A muffling device for exhausting at least one fluid flow in a gas turbine engine includes a first diffuser coupled in flow communication with a first conduit. The first diffuser is configured to exhaust a first fluid flow. The device further includes a second diffuser disposed adjacent the first diffuser. The second diffuser is coupled in flow communication with a second conduit. The second diffuser is configured to exhaust a second fluid flow. The device also includes a third diffuser at least partially surrounding the first diffuser and the second diffuser. The third diffuser is coupled in flow communication with the first diffuser and the second diffuser. The third diffuser includes a body with apertures and is configured to exhaust a third fluid flow. The third fluid flow includes at least one of the first fluid flow and the second fluid flow.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: October 30, 2018
    Assignee: General Electric Company
    Inventors: John Carl Glessner, Jarrod Paul Sands
  • Patent number: 10113559
    Abstract: A gas turbine engine impact liner is disclosed. The impact liner may include a base sheet, a plurality of stanchions extending from the base sheet, and a plurality of supports, each being operatively associated with one of the plurality of stanchions.
    Type: Grant
    Filed: September 10, 2015
    Date of Patent: October 30, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew A. Turner, Colin J. Kling, David A. Topol
  • Patent number: 10107198
    Abstract: An oil supply system for a gas turbine engine has a lubricant pump delivering lubricant to an outlet line. The outlet line is split into at least a hot line and into a cool line, with the hot line directed primarily to locations associated with an engine that are not intended to receive cooler lubricant, and the cool line directed through one or more heat exchangers at which lubricant is cooled. The cool line then is routed to a fan drive gear system of an associated gas turbine engine. A method and apparatus are disclosed. The heat exchangers include at least an air/oil cooler wherein air is pulled across the air/oil cooler to cool oil. The air/oil cooler is provided with an ejector tapping compressed air from a compressor section to increase airflow across the air/oil cooler.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: October 23, 2018
    Assignee: United Technologies Corporation
    Inventors: Ethan K. Stearns, Jorn A. Glahn, Daniel J. McKaveney
  • Patent number: 10107498
    Abstract: Embodiments of the present disclosure provide injection systems for fuel and air. According to one embodiment, an injection system can include a mixing zone embedded within a surface of a turbine nozzle and positioned between a first outlet and a second outlet, the turbine nozzle separating a combustor of a power generation system from a turbine stage of the power generation system, wherein the first outlet is oriented substantially in opposition to the second outlet; a first injection conduit for delivering a carrier gas to the mixing zone through the first outlet; and a second injection conduit for delivering a fuel to the mixing zone through a second outlet; wherein the carrier gas and the fuel intermix within the mixing zone upon leaving the first injection conduit and the second injection conduit.
    Type: Grant
    Filed: December 11, 2014
    Date of Patent: October 23, 2018
    Assignee: General Electric Company
    Inventors: Stanley Kevin Widener, Lewis Berkley Davis, Jr., Gregory Thomas Foster, Kaitlin Marie Graham, Krishnakumar Venkataraman
  • Patent number: 10107501
    Abstract: An object is to realize combustion flame which can further reduce the amount of NOx generation. A combustor (14) includes a pilot nozzle (40); a plurality of main nozzles (44) arranged apart from the pilot nozzle (40) in the circumferential direction on the outer peripheral side of the pilot nozzle (40) and configured to perform premix combustion; a combustor basket (34) surrounding the pilot nozzle (40) and each main nozzle (44); an outlet outer ring (50) provided at a tip end of the combustor basket (34); and a combustion liner (36) fitted, at an inner surface thereof, onto the outer periphery of the combustor basket (34) and surrounding the outlet outer ring (50). The outlet outer ring (50) is formed parallel to an inner wall surface (66) of the combustion liner (36).
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: October 23, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Takiguchi, Mitsunori Isono, Atsushi Yuasa, Eisaku Ito, Shigemi Mandai
  • Patent number: 10101033
    Abstract: An engine includes an elongated pulse detonation combustor tube having an arcuate combustion path over a majority of an entire length of the combustor tube, and an elongated portion of the combustor tube being oriented transverse to a central axis of the engine.
    Type: Grant
    Filed: December 17, 2014
    Date of Patent: October 16, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James D. Hill, Michael J. Cuozzo
  • Patent number: 10100738
    Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: October 16, 2018
    Assignee: United Technologies Corporation
    Inventors: James D. Hill, William K. Ackermann
  • Patent number: 10100747
    Abstract: A fuel supply system for use in a gas turbine engine is provided. The fuel supply system includes a fuel manifold, and a shutoff valve coupled in flow communication with the fuel manifold and positioned upstream from said fuel manifold. The shutoff valve is configured to actuate into a closed position when the gas turbine engine is operating at an overspeed condition. The system also includes a relief valve coupled in flow communication with the fuel manifold, wherein the relief valve is configured to release fuel from within the fuel manifold when the shutoff valve is in the closed position, and when a pressure within the fuel manifold is greater than a first predetermined threshold.
    Type: Grant
    Filed: November 18, 2015
    Date of Patent: October 16, 2018
    Assignee: General Electric Company
    Inventors: Alberto Jose Negroni, David August Snider, William Forrester Seely, Keegan Saunders O'Donnell, Kyle Joseph Conger, Carlos Gabriel Roman
  • Patent number: 10094235
    Abstract: One embodiment of the present invention is a unique vehicle. Another embodiment is a unique propulsion system. Yet another embodiment is a unique system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for vehicle propulsions systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: January 27, 2015
    Date of Patent: October 9, 2018
    Assignee: Rolls-Royce Corporation
    Inventor: Donald W. Burns
  • Patent number: 10098191
    Abstract: An inductively coupled plasma device includes a rotary furnace tube and an inductively coupled plasma source. The rotary furnace tube has a first end, a second end and a longitudinal axis. In a first embodiment, the inductively coupled plasma source is disposed proximate to the first end of the rotary furnace tube and is aligned with the longitudinal axis of the rotary furnace such that the inductively coupled plasma source discharges a plasma into the rotary furnace tube. In a second embodiment, the inductively coupled plasma source is a ground electrode disposed within and aligned with the longitudinal axis of the rotary furnace tube, and a second electromagnetic radiation source disposed around or within the rotary furnace tube that generates a wave energy. The inductively coupled plasma source discharges a plasma within the rotary furnace tube.
    Type: Grant
    Filed: December 4, 2014
    Date of Patent: October 9, 2018
    Assignee: Forest Plasma Labs, LLC
    Inventor: Todd Foret
  • Patent number: 10094233
    Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track. The inserts are bonded to an annular runner also included in the blade track by a braze layer.
    Type: Grant
    Filed: December 3, 2013
    Date of Patent: October 9, 2018
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Sean E. Landwehr, William Westphal, Ted J. Freeman, Adam L. Chamberlain
  • Patent number: 10094281
    Abstract: A gas turbine engine comprises a fan on an engine central axis. Plural gas generators are downstream of the fan, each along a respective central axis, mutually offset, and offset from the engine central axis. A fan drive turbine is on the engine central axis, downstream of the dual gas generators, and driven by output from the dual gas generators, to drive the fan.
    Type: Grant
    Filed: January 13, 2015
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Jesse M. Chandler, Gabriel L. Suciu
  • Patent number: 10087845
    Abstract: A manifold pressure damping assembly that includes one or more closed volumes coupled in flow communication with a manifold through one or more flow restrictors is provided.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: October 2, 2018
    Assignee: General Electric Company
    Inventor: Xilin Yang
  • Patent number: 10087887
    Abstract: A system for the recovery and management of atmospheric gas is disclosed, such as for use as a vehicle propellant in a vehicle propulsion system. The system can include a compressor configured to compress atmospheric gas and first and second storage tanks configured to store liquefied atmospheric gas from the compressor. The second storage tank can have a heater operable to heat liquefied atmospheric gas therein to convert it to a high pressure gas. The second storage tank includes an outlet duct fluidly coupled to the first storage tank for supplying high pressure gas to the first storage tank.
    Type: Grant
    Filed: July 27, 2011
    Date of Patent: October 2, 2018
    Assignee: AIRBUS DEFENCE AND SPACE LIMITED
    Inventor: Jaime Simon Reed
  • Patent number: 10082082
    Abstract: A fuel injector for a gas turbine engine is disclosed. The fuel injector includes a flange assembly with a distribution block, three main gas tubes, and an injector head. The distribution block evenly distributes a main gas fuel to the three main gas tubes. The injector head includes an injector body with a primary gas gallery including an annular shape. The three main gas tubes are connected in a parallel configuration between the distribution block and the primary gas gallery. The three main gas tubes are all in flow communication with the primary gas gallery and provide the main gas fuel from the same main gas fuel source.
    Type: Grant
    Filed: January 5, 2016
    Date of Patent: September 25, 2018
    Assignee: Solar Turbines Incorporated
    Inventors: Sean Kelly Spivey, Donald James Cramb, James Scott Piper, Michael John Ramotowski
  • Patent number: 10082085
    Abstract: A gas turbine engine assembly includes a support component, an engine component, and a seal. The annular support component is formed to include a notch. The engine component is mounted in spaced-apart relation to the support component so that a gap is formed between the support component and the engine component. The seal is located in the notch and is adapted to close the gap.
    Type: Grant
    Filed: November 17, 2014
    Date of Patent: September 25, 2018
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman
  • Patent number: 10077903
    Abstract: Aspects of the disclosure are directed to a cooling design feature for inclusion in a liner of an aircraft, comprising: a plurality of angled holes, and at least one through hole separating all combinations of any two of the angled holes, wherein the at least one through hole is oriented at an angle that is substantially perpendicular to a surface of the liner, and wherein each of the plurality of angled holes are non-parallel to the at least one through hole.
    Type: Grant
    Filed: October 19, 2015
    Date of Patent: September 18, 2018
    Assignee: United Technologies Corporation
    Inventors: John S. Tu, James B. Hoke, Monica Pacheco-Tougas, Timothy S. Snyder, Dennis M. Moura, Anthony Van
  • Patent number: 10072572
    Abstract: A gas turbine engine. The engine includes a first compressor coupled to a first turbine by a first shaft, the first turbine having first and second turbine stages. A first combustor is provided downstream of the first compressor and upstream of the first stage of the first turbine. A second combustor is provided downstream of the first stage of the first turbine, and upstream of the second stage of the first turbine. A further turbine is provided downstream of the first turbine, and is coupled to a further compressor by a further shaft.
    Type: Grant
    Filed: March 16, 2015
    Date of Patent: September 11, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Ahmad Razak
  • Patent number: 10072515
    Abstract: The disclosure relates Frame segment for a transition piece-turbine interface having a picture frame receptacle for axially receiving an aft end of a combustor transition piece. The frame segment can include an I-beam with an upper horizontal element, a lower horizontal element, and a vertical web, wherein the upper horizontal element has mounting face for fixation to a vane carrier. The vertical web has a downstream face, facing towards a first stage of a turbine when installed in a gas turbine. The vertical web includes a cooling gas duct for supplying cooling gas to the downstream face of the vertical web.
    Type: Grant
    Filed: November 23, 2015
    Date of Patent: September 11, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Fabien Fleuriot, Hans-Christian Mathews