Patents Examined by Thuyhang N Nguyen
  • 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: 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: 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: 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: 10941940
    Abstract: A burner for a gas turbine, having a combustion chamber, a first injector adapted to inject a first fuel into the combustion chamber and a second injector adapted to inject a second fuel being less reactive than the first fuel into the combustion chamber, wherein the burner is adapted to premix the fuels with an air flow before the fuel enter the reaction zone of the combustion chamber such that a first fuel flow of the first fuel has a first premixing stream line and a second fuel flow of the second fuel has a second premixing stream line, wherein each of the premixing stream lines begins with the beginning of the premixing with the air flow and ends at the location where the fuel enters the reaction zone and the length of the second premixing stream line is longer than the length of the first premixing stream line.
    Type: Grant
    Filed: July 4, 2016
    Date of Patent: March 9, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Ghenadie Bulat, Jonathan May
  • Patent number: 10940938
    Abstract: A system for changing the pitch of blades of at least one turbomachine rotor is provided. The system generally includes a control means acting on a connecting mechanism connected to the blades of the rotor and having a body mobile in translation along a longitudinal axis with respect to a fixed body, load-transfer bearing mounted on the mobile body cooperating with the connecting mechanism, and means for lubricating the bearing having a lubricant duct and extending radially above the fixed and mobile bodies. The duct generally includes first and second telescopic tubular parts that slide coaxially with respect to one another, the first part connected to the fixed body and the second part connected to the mobile body, and means for spraying lubricant into the bearing mounted on the mobile body and lubricant supply conduit mounted on the mobile body to connect the duct to the spraying means.
    Type: Grant
    Filed: August 16, 2017
    Date of Patent: March 9, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Régis Eugène Henri Servant, Anthony Lafitte, Eddy Keomorakott Souryavongsa, Sébastien Emile Philippe Tajan, Arnaud Martin
  • Patent number: 10935242
    Abstract: A gas turbine engine and combustor assembly is generally provided. The gas turbine engine may include an outer casing while the combustor assembly may include a liner and a damper assembly. The liner may at least partially define a combustion chamber extending between an aft end and a forward end generally along an axial direction within the outer casing. The liner may include an inner surface facing the combustion chamber and an outer surface facing away from the combustion chamber. The damper assembly may extend between the outer casing and the outer surface of the liner. The damper assembly may include a selectively separable support and damper spring. The damper spring may be disposed between the support and the liner.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: March 2, 2021
    Assignee: General Electric Company
    Inventors: Mark Willard Marusko, Michael Alan Stieg, Brian Christopher Towle
  • Patent number: 10934886
    Abstract: The present invention concerns a method (200) for managing a breakdown of a starter valve of a starting circuit of an aircraft turbine engine, comprising the following steps: —starting (203) the turbine engine, a state-change command being sent to the starter valve in order for it to open; —increasing (204) the engine speed of the turbine engine to a predefined first threshold, —during said increase (204) in engine speed, —if a difference in position has been detected (201) between the position sensors before the step of starting the turbine engine or if a difference in position is detected (205) between said position sensors, determining (207) the position sensor that has switched between the closed position and the open position, the other position sensor having remained in the open or closed position; —when the first threshold is reached, storing (209) the position sensor that has switched between the closed position and the open position as healthy and the position sensor that has remained in the open or
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Adel Cedric Abir Widemann, David Julien Boyer
  • Patent number: 10927687
    Abstract: A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.
    Type: Grant
    Filed: December 3, 2018
    Date of Patent: February 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Chris Vargas, Robert Russell Mayer
  • Patent number: 10927679
    Abstract: The present disclosure provides methods, assemblies, and systems for power production that can allow for increased efficiency and lower cost components arising from the control, reduction, or elimination of turbine blade mechanical erosion by particulates or chemical erosion by gases in a combustion product flow. The methods, assemblies, and systems can include the use of turbine blades that operate with a blade velocity that is significantly reduced in relation to conventional turbines used in typical power production systems. The methods and systems also can make use of a recycled circulating fluid for transpiration protection of the turbine and/or other components. Further, recycled circulating fluid may be employed to provide cleaning materials to the turbine.
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: February 23, 2021
    Assignee: 8 Rivers Capital, LLC
    Inventors: Miles R. Palmer, Jeremy Eron Fetvedt, Rodney John Allam
  • Patent number: 10920670
    Abstract: A sealing arrangement at an interface between a combustor and a turbine of a gas turbine. The turbine can include deflecting vanes at its inlet, which deflecting vanes are each mounted within the turbine so as to define an inner or outer diameter platform and are in sealing engagement via an inner or outer diameter vane tooth with a seal arranged at the corresponding inner or outer diameter part of the outlet of the combustor. The seal is movable and is pressed on the inner or outer diameter vane tooth by a differential pressure such that the pressure of the mainstream hot gas flow is a lower pressure.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: February 16, 2021
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Marcos Escudero Olano, Stephan Strueken, Thomas Zierer, Frank Graf, Adnan Eroglu, Joshua R. McNally, Stephen W. Jorgensen, Afzal Pasha Mohammed
  • Patent number: 10914200
    Abstract: A CCPP includes a gas turbine, a HRSG, a steam turbine a flash tank and first and second supply lines. The gas turbine, the HRSG and the steam turbine are interconnected to generate power. The gas turbine may include an air preheating system to preheat the air supplied in the gas turbine to enable expedite combustion therein. The flash tank is fluidically connected at a cold end of the HRSG to extract waste hot water from the cold end. Further, the first supply line is configured to interconnect the flash tank and the steam turbine to supply of flash steam to the steam turbine. Furthermore, the second supply line is configured to interconnect the flash tank and the air preheating system to supply hot flash condensate thereto.
    Type: Grant
    Filed: October 24, 2014
    Date of Patent: February 9, 2021
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Klara Berg, Mariah Couzzi-Carneiro, Paul Drouvot, Torbjörn Stenström
  • Patent number: 10914202
    Abstract: A water/steam system for a combined cycle power plant and related method for operating said system are provided. The system comprises a heat recovery steam generator providing a flue gas stream path for extracting heat from a flue gas stream exhausted from a gas turbine, the heat recovery steam generator having a low pressure section including a low pressure evaporator arranged along the flue gas stream path for generating low pressure steam at a low pressure input level for a main input of a low pressure steam turbine. To use heat at low temperatures, the low pressure section may include a sub low pressure subsection with a sub low pressure evaporator for generating sub low pressure steam, at a sub low pressure level below the low pressure input level. The sub low pressure evaporator is disposed in the flue gas stream path downstream of a low pressure economizer.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: February 9, 2021
    Assignee: General Electric Technology GmbH
    Inventors: Mariah Couzzicarneiro, Joerg Dietzmann
  • Patent number: 10907578
    Abstract: Systems and methods are provided for an air-driven augmentor fan equipped aircraft propulsor. The augmentor fan may increase the effective bypass ratio of the aircraft propulsor and reduce fuel consumption and carbon emissions of the aircraft. The augmentor fan may be driven by air energized by a ducted fan powered by the core engine of the aircraft propulsor. The energized air may be received by an inlet, flowed through a flow path, and exhausted out the outlet to drive the augmentor fan. The exhausted energized air may impart a torque on the augmentor fan or blades of the augmentor fan. One or more of the inlet, flow path, or outlet may be variable in size to control the volume of air flowed through the flow path.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: February 2, 2021
    Assignee: The Boeing Company
    Inventor: Mithra M. K. V. Sankrithi
  • Patent number: 10907824
    Abstract: A fuel split control arrangement is provided. The arrangement includes a staged cooling flow control valve and cooling check valve. The staged cooling flow control valve and cooling check valve is connected between the primary and secondary tips of a nozzle in a turbine engine. The staged cooling flow control valve and cooling check valve includes a valve member arrangement operable to prevent fuel flow from the secondary fuel supply manifold to the secondary tip and simultaneously allow fuel flow from the secondary fuel supply manifold to the primary tip such that the primary tip receives fuel flow from both the secondary fuel supply manifold and the primary fuel supply manifold.
    Type: Grant
    Filed: August 17, 2012
    Date of Patent: February 2, 2021
    Assignee: Woodward, Inc.
    Inventors: Brett Jay Snodgrass, Charlie Carson, Carthel C. Baker, Michael P. Garry
  • Patent number: 10900664
    Abstract: A fuel gas nozzle used in a microturbine includes a first chamber, a second chamber connected to the first chamber, a pilot fuel gas pipe, a main fuel gas pipe and an intake pipe. An intake zone and a mixing zone are respectively formed in the first chamber and the second chamber and are communicated with each other. The pilot fuel gas pipe is for introducing a first fuel gas into a downstream of the second chamber. The main fuel gas pipe is for introducing a second fuel gas into the mixing zone via the intake zone. The intake pipe is for introducing an air into the mixing zone. A centerline of the intake pipe is not intersected with a centerline of the second chamber, so as to induce a vortex flow field of the air flowing into the mixing zone for mixing the air and the second fuel gas.
    Type: Grant
    Filed: December 21, 2018
    Date of Patent: January 26, 2021
    Assignee: National Chung-Shan Institute of Science and Technology
    Inventors: Yung-Mao Tsuei, Chih-Chuan Lee, Chi-Fang Chiu
  • Patent number: 10876419
    Abstract: A conjunction assembly provides a seal, in a connected state, between a conjunction ring constituting an outlet of a combustor and a turbine inlet cylinder constituting an inlet of the turbine. The conjunction assembly includes a connecting member that protrudes from the conjunction ring; a connecting groove for receiving the connecting member, the connecting groove formed in the turbine inlet cylinder; and a connection sealing member disposed between the connecting member and an inner surface of the turbine inlet cylinder to provide a seal between the connecting member and the inner surface of the turbine inlet cylinder. The connecting member is a ring-like structure formed on a rear-side surface of the conjunction ring, the rear-side surface facing the turbine inlet cylinder, and the connecting groove is formed in a front-side surface of the turbine inlet cylinder in correspondence to the connecting member, the front-side surface facing the conjunction ring.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: December 29, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Dong Hwa Kim
  • Patent number: 10871127
    Abstract: An extended expander cycle system comprising a rocket engine having a plurality of channels; a plurality of fuel supplied one-wheel-turbopumps; a plurality of oxidizer supplied one-wheel-turbopumps; wherein utilization of the plurality of channels for both fuel and oxidizer and utilization of plurality of fuel and oxidizer supplied one-wheel-turbopumps provides adequate energy for fuel and oxidizer pressurization.
    Type: Grant
    Filed: July 19, 2018
    Date of Patent: December 22, 2020
    Inventor: Nadir T Bagaveyev
  • Patent number: 10865992
    Abstract: A fuel injector is provided for the radial introduction of a fuel/air mixture to a combustor. The fuel injector includes a frame having interior sides defining an opening for passage of a first fluid; at least one fuel injection body; and a conduit fitting. The at least one fuel injection body is coupled to the frame and positioned within the opening, thereby defining flow paths for the first fluid. The at least one fuel injection body defines a fuel plenum, and a set of fuel injection holes are defined through an outer surface of the at least one fuel injection body. The conduit fitting is coupled to the frame and conveys fuel from a fuel supply line to the fuel plenum. Fuel and the first fluid mix in the flow paths and are delivered through the outlet to the combustor.
    Type: Grant
    Filed: December 30, 2016
    Date of Patent: December 15, 2020
    Assignee: General Electric Company
    Inventors: Richard Martin DiCintio, Seth Reynolds Hoffman, Ronnie Ray Pentecost, Jayaprakash Natarajan, Wei Zhao
  • Patent number: 10859002
    Abstract: Disclosed herein is a method for controlling a surge margin of a gas turbine and an extraction device for a gas turbine. The method for controlling the surge margin of the gas turbine and the extraction device for the gas turbine may support stable operation of a compressor unit in the gas turbine, thereby improving the efficiency of the gas turbine and minimizing vibration and noise of the gas turbine.
    Type: Grant
    Filed: January 23, 2018
    Date of Patent: December 8, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Sang Jo Kim