Patents Examined by Todd E. Manahan
  • Patent number: 11002142
    Abstract: A variable vane assembly including a variable stator vane disposed in a main flow gaspath, the variable stator vane having a vane stem. The assembly also includes a case located at a radially outward location of the variable stator vane, the vane stem extending through a port of the case, the port defined by a port wall, a clearance defined by the vane stem and a port wall to allow gas from the main flow gaspath to pass therethrough. The assembly further includes a synchronization ring spaced from the case to define a gap. The assembly yet further includes a vane arm operatively coupled to a synchronization ring and to the vane stem, the vane arm redirecting gas from the main flow gaspath to the synchronization ring.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: May 11, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tristan Thomas Peirce
  • Patent number: 11002225
    Abstract: An air-breathing rocket engine in certain embodiments comprises an hourglass-shaped outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake that terminates in a floor and an inner front wall that forms a first circumferential gap between the inner front wall and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector polis and one or more ignition ports are situated at the front end of the second circumferential gap.
    Type: Grant
    Filed: March 24, 2020
    Date of Patent: May 11, 2021
    Assignee: Mountain Aerospace Research Solutions, Inc.
    Inventors: Aaron Davis, Scott Stegman
  • Patent number: 11002192
    Abstract: A system for producing high purity carbon monoxide and hydrogen as well as activated carbon includes a pyrolysis reactor, a gasifier, a combustion turbine, a boiler, a steam turbine, a combined cycle unit and an electrolysis unit. Liquid fuel from the pyrolysis reactor is provided to the combustion turbine. Liquid and gaseous fuels are provided to the boiler. Compressed oxygen from the electrolysis unit is provided to the combustion turbine. Electric power from the combustion turbine and steam turbine are provided to the electrolysis unit. The gasifier includes a preheat region, a gasification region, and a cooling region. CO2 and O2 are injected into the gasifier at multiple injection levels to create an isothermal gasification region to produce CO. The CO2 and O2 are preheated in a heat exchanger using the CO exiting from the gasifier prior to injection.
    Type: Grant
    Filed: September 30, 2020
    Date of Patent: May 11, 2021
    Assignee: ARB Pyrolysis, LLC
    Inventors: Mack D. Bowen, Robert G. Kelly
  • Patent number: 10995698
    Abstract: A mixer assembly group for a turbofan engine, having a primary flow channel extending along a central axis of the turbofan engine and a secondary flow channel. The mixer assembly group includes a mixer for guiding a first fluid flow from the primary flow channel and a second fluid flow from the secondary flow channel in the direction of an exhaust of the turbofan engine, as well as for intermixing the first and second fluid flows, and a connection appliance, which has at least one connection component that is fixated at the mixer and by means of which the mixer assembly group is to be fixated at two different first and second engine components of the turbofan engine, with are subject to operating temperatures of different heights during operation of the turbofan engine.
    Type: Grant
    Filed: September 6, 2017
    Date of Patent: May 4, 2021
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Predrag Todorovic, Thomas Kubisch
  • Patent number: 10995669
    Abstract: Disclosed herein are a nozzle capable of efficiently atomizing fuel, a combustor, and a gas turbine. The nozzle for the combustor includes a tube assembly including an air passage through which air moves, a main fuel passage disposed inside the air passage so that main fuel moves through the main fuel passage, and a pilot fuel passage disposed inside the main fuel passage so that pilot fuel moves through the pilot fuel passage as well as a nozzle tip configured to eject the pilot fuel and the main fuel, where the nozzle tip includes an injection passage coupled with the pilot fuel passage and a plurality of centrifugal flow chambers disposed outside the injection passage and communicating with the main fuel passage.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: May 4, 2021
    Inventors: Alexander Myatlev, Hanjin Jeong, Borys Shershnyov
  • Patent number: 10995703
    Abstract: A pulse combustor system for reducing noise and/or vibration levels. The system includes a pulse combustor including a combustion chamber, an inlet pipe, an exhaust pipe, and a first fuel injector for injecting fuel into the combustion chamber. The pulse combustor has a fundamental oscillation mode and one or more additional oscillation modes. The system includes at least one pressure sensor for measuring a pressure inside the fuel combustor and/or a at least one fluid velocity sensor for measuring fluid velocity at the inlet pipe or at the exhaust pipe. A controller adjusts a rate of fuel supply to the pulse combustor if the measured pressure and/or the measured velocity is above a predetermined threshold value to reduce excitation of the one or more additional oscillation modes.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: May 4, 2021
    Assignee: NORTH AMERICAN WAVE ENGINE CORPORATION
    Inventor: Daanish Maqbool
  • Patent number: 10989413
    Abstract: The present disclosure is directed to an axial retention assembly for combustor components of a gas turbine engine. The axial retention assembly may include a combustor having a liner and a casing, with the casing including a flange spaced apart from the liner along an axial centerline of the combustor. Furthermore, the axial retention assembly may include a mounting plate having a first end removably coupled to the flange and a second end positioned inward from the casing in a radial direction. Moreover, the axial retention assembly may include a clamp removably coupled to the liner. Additionally, the axial retention assembly may include a tie rod coupled to the second end of the mounting plate and the clamp to reduce relative movement between the liner and the casing along the axial centerline.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: April 27, 2021
    Assignee: General Electric Company
    Inventors: Stuart Craig Hanson, Thomas Alan Mogle, II
  • Patent number: 10989118
    Abstract: Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: April 27, 2021
    Assignee: WRIGHTSPEED, INC.
    Inventors: Ian Wright, Brandon Stitt
  • Patent number: 10988265
    Abstract: Disclosed is an apparatus for protecting an engine of an aircraft to prevent an inlet of an engine of an aircraft from being damaged. The apparatus includes: a protective net attached to an inlet arranged at a front of the engine of the aircraft; and hangers configured to fix the protective net along a side surface of the engine, wherein the protective net includes a plurality of circular fibers concentrically arranged while forming a circle, and a fixing fiber configured to fix an outer peripheral surface of the circular fibers to an outer surface of the engine while being bound to inner surfaces of the circular fibers and passing through a center of the circular fibers.
    Type: Grant
    Filed: July 17, 2019
    Date of Patent: April 27, 2021
    Inventors: Yoon-ki Baek, Yu-dam Baek
  • Patent number: 10982625
    Abstract: A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.
    Type: Grant
    Filed: August 6, 2018
    Date of Patent: April 20, 2021
    Assignee: Goodrich Corporation
    Inventors: Paul Parinas, Brian Wilson
  • Patent number: 10982857
    Abstract: A nozzle, a combustor, and a gas turbine are capable of uniformly pre-mixing fuel and air. The nozzle includes an integrated swirler comprising an inner tube configured to provide a first pre-mixing passage through which pre-mixed air flows, an outer tube configured to partially enclose the inner tube and form an outer fuel passage through which fuel flows, and a plurality of vanes coupled with the outer tube, each vane having an exhaust hole through which fuel exits; a fuel injector including an inner fuel passage through which fuel flows and being configured to be inserted into the inner tube of the integrated swirler; and a peg having an outer surface in which are formed a plurality of injection holes communicating with the inner fuel passage, the injection holes configured to inject the fuel of the inner fuel passage into the first pre-mixing passage.
    Type: Grant
    Filed: December 20, 2018
    Date of Patent: April 20, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Yunyoung Doh, Muhwan Chon, Borys Shershnyov
  • Patent number: 10975804
    Abstract: A flow control device includes a first axially extending flow control surface, a second axially extending flow control surface radially offset from the first surface to define a gas flow path therebetween, the gas flow path having a downstream flow path exit, and a third axially extending flow control surface radially offset from the first surface and capable of axially translating with respect to the first and second surfaces for modifying the gas flow path and selectively closing the flow path exit. A turbofan engine includes a core flow passage, a fan bypass passage located radially outward from the core flow passage, a third stream bypass passage located radially outward from the fan bypass passage, and a flow control device that dynamically regulates the third stream bypass passage, allowing fluid flowing through the third stream bypass passage to provide thrust to the turbofan engine and reduce afterbody drag.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: April 13, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: John R. Buey, Robert H. Bush, Felix Izquierdo
  • Patent number: 10968865
    Abstract: A rocket propulsion system comprises a combustion chamber, an oxygen supply system, comprising an oxygen supply duct and being configured to supply oxygen to the combustion chamber, and a hydrogen supply system, comprising a hydrogen supply duct and being configured to supply hydrogen to the combustion chamber. An ignition unit of the propulsion system, to which at least portions of the oxygen and the hydrogen supplied to the combustion chamber can be supplied, is configured to initiate combustion of the oxygen-hydrogen mixture in the combustion chamber. The propulsion system further comprises a cooling duct extending along an inner surface of a combustion chamber wall and through which at least a portion of the oxygen supplied to the combustion chamber, at least a portion of the hydrogen supplied to the combustion chamber or a combustion gas mixture emerging from the ignition unit flows.
    Type: Grant
    Filed: May 17, 2017
    Date of Patent: April 6, 2021
    Assignee: ARIANEGROUP GMBH
    Inventors: Ulrich Gotzig, Malte Wurdak, Joel Deck, Manuel Frey
  • Patent number: 10968749
    Abstract: A combustion chamber arrangement includes an annular combustion chamber, a plurality of lean burn fuel injectors and a stage of turbine nozzle guide vanes. The stage of turbine nozzle guide vanes is arranged at the downstream end of the annular combustion chamber and includes a plurality of circumferentially spaced vanes extending between and being secured to an annular inner wall and an annular outer wall. The annular inner wall has an outer surface which has a plurality of outer surface portions and each portion is positioned between a pair of circumferentially adjacent vanes and the annular outer wall has an inner surface which has a plurality of inner surface portions and each portion is positioned between a pair of circumferentially adjacent vanes.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: April 6, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Shahrokh Shahpar, John Coull, Matthew Symes
  • Patent number: 10968837
    Abstract: Embodiments of systems and methods for air recovery are disclosed. The diverted pressurized air may be used to supply a hydrostatic purge to the unutilized portion of a turbine engine fuel manifold circuit to ensure that exhaust gases from the utilized side of the fuel manifold circuit do not enter the portion of the alternative fuel manifold circuit rack. The assembly used to remove compressor section pressurized air may include a flow control orifice, line pressure measuring instrumentation, non-return valves, isolation valves and hard stainless-steel tubing assemblies. In some embodiments, a turbine compressor section diverter system may include a small air receiver used to increase the volume of air supplying the manifold to aid in potential pressure and flow disruptions from a turbine engine compressor section.
    Type: Grant
    Filed: May 21, 2020
    Date of Patent: April 6, 2021
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
  • Patent number: 10961952
    Abstract: An air-breathing rocket engine with an hourglass-shaped outer shell and an interior portion situated entirely within the front end of the outer shell. The interior portion includes a funnel-shaped intake that terminates in a floor and an inner front wall that forms a first circumferential gap between the inner front wall and the outer surface of the funnel-shaped intake. The intake has a central aperture that is in fluid communication with the throat and exhaust areas within the outer shell. A second circumferential gap is formed between the outer surface of the front inner wall and the inner surface of the front end of the outer shell and is in fluid communication with the throat and exhaust areas within the outer shell. One or more injector ports and one or more ignition ports are situated at the front end of the second circumferential gap.
    Type: Grant
    Filed: January 29, 2020
    Date of Patent: March 30, 2021
    Assignee: Mountain Aerospace Research Solutions, Inc.
    Inventors: Aaron Davis, Scott Stegman
  • Patent number: 10961908
    Abstract: Systems and methods to increase intake air flow to a gas turbine engine of a hydraulic fracturing unit when positioned in an enclosure may include providing an intake expansion assembly to enhance intake air flow to the gas turbine engine. The intake expansion assembly may include an intake expansion wall defining a plurality of intake ports positioned to supply intake air to the gas turbine engine. The intake expansion assembly also may include one or more actuators connected to a main housing of the enclosure and the intake expansion assembly. The one or more actuators may be positioned to cause the intake expansion wall to move relative to the main housing between a first position preventing air flow through the plurality of intake ports and a second position providing air flow through the plurality of intake ports to an interior of the enclosure.
    Type: Grant
    Filed: June 15, 2020
    Date of Patent: March 30, 2021
    Assignee: BJ Energy Solutions, LLC
    Inventors: Tony Yeung, Ricardo Rodriguez-Ramon, Joseph Foster
  • Patent number: 10954892
    Abstract: A liquid propellant rocket engine includes a combustion chamber that has a throat and a nozzle aft of the throat. The nozzle has a first nozzle section adjacent the throat and a second nozzle section aft of the first nozzle section. The first nozzle section includes active cooling features and the second nozzle section excludes any active cooling features. The first nozzle section is operative via at least the active cooling features to form a condensate that passively cools the second nozzle section.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: March 23, 2021
    Assignee: AEROJET ROCKETDYNE, INC.
    Inventors: Jiten R. Patel, Jim A. Clark, Charles Whipple, IV
  • Patent number: 10954858
    Abstract: A plate fin heat exchanger is disclosed. The heat exchanger includes a plurality of plates defining a set of hot fluid passages between adjacent plates of the plurality of plates and a set of cold fluid passages between adjacent plates of the plurality of plates. A hot fluid inlet and outlet are located at a first face of the heat exchanger. A barrier is located between adjacent plates defining the hot fluid passages. The barrier extends between the adjacent plates and extends from the first face of the heat exchanger at a location between the hot fluid inlet and the hot fluid outlet in a direction perpendicular to the first face, and defines a first pass of hot fluid passages on a first side of the barrier and a second pass of hot fluid passages on a second side of the barrier.
    Type: Grant
    Filed: June 18, 2015
    Date of Patent: March 23, 2021
    Assignee: HAMILTON SUNSTRAND CORPORATION
    Inventors: Donald E. Army, Jr., Michael Doe, Jr., Kurt L. Stephens
  • Patent number: 10947898
    Abstract: A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: March 16, 2021
    Assignee: General Electric Company
    Inventors: William Scott Zemitis, Richard Ryan Pilson, Melbourne James Myers, Dustin Jaime Muller