Patents Examined by Scott J Walthour
  • Fuel injector
    Patent number: 11162682
    Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel stem assembly for receiving and distributing fuel and an injector head receiving fuel from the fuel stem assembly. The injector head can include an injector body, swirler vanes, a pilot assembly, passages, and fuel galleries. The pilot assembly can include pilot struts and a pilot tube. The swirler vanes and pilot struts can include passages to transport the pilot fuel from the fuel stem assembly to the pilot tube.
    Type: Grant
    Filed: October 11, 2019
    Date of Patent: November 2, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: Richard A. Rogers, Drew Allen Dominique, Timothy Ray Evans, Jr., Jonathan Gerrard Duckers, Stephen Burke, Robert Archer, Stefan Helmuth Humer, Hanjie Lee
  • Fluid injection systems having fluid line purging
    Patent number: 11156163
    Abstract: A fluid injection system can include a main flow line, a primary flow line connected to the main flow line, and a primary flow valve disposed between the primary flow line and the main flow line and configured to allow injectant flow to the primary flow line from the main flow line in an open primary flow valve state, and to prevent injectant flow to the primary flow line from the main flow line in a closed primary flow valve state. The system can include a secondary flow line connected to the main flow line and a secondary flow valve disposed between the secondary flow line and the main flow line and configured to selectively allow injectant flow to the secondary flow line from the main flow line in an open secondary flow valve state, and to prevent injectant flow to the secondary flow line from the main flow line in a closed secondary flow valve state.
    Type: Grant
    Filed: October 4, 2019
    Date of Patent: October 26, 2021
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Ryan Susca, Steve Doerner, Charles E. Reuter
  • Heat exchanger mounted at rear of gas turbine engine for challenging temperature applications
    Patent number: 11149643
    Abstract: A gas turbine engine has a fan rotor delivering air into a bypass duct defined between an outer fan case and an outer interior housing. The fan rotor also delivers air into a compressor section, a combustor, a turbine section. A chamber is defined between the outer interior housing and an inner housing. The inner housing contains the compressor section, the combustor and the turbine section. A first conduit taps hot compressed air to be cooled and passes the air to at least one heat exchanger. The air is cooled in the heat exchanger and returned to a return conduit. The return conduit passes the cooled air to at least one of the turbine section and the compressor section. The heat exchanger has a core exhaust plane. The turbine section has at least a first and a downstream second rotor blade row, with the core exhaust plane located downstream of a center plane of the second blade row.
    Type: Grant
    Filed: December 5, 2016
    Date of Patent: October 19, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, Nathan Snape
  • Heat exchange module for a turbine engine
    Patent number: 11149644
    Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.
    Type: Grant
    Filed: March 21, 2019
    Date of Patent: October 19, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Frederick M. Schwarz, John T. Schmitz
  • Main mixer in an axial staged combustor for a gas turbine engine
    Patent number: 11149952
    Abstract: A main mixer including a swirler along an axis, the swirler including an outer swirler with a multiple of outer vanes, and a center swirler with a multiple of center vanes and a swirler hub along the axis, the swirler hub including a fuel manifold and an inner swirler with a multiple of inner vanes that support a centerbody, the multiple of inner vanes interconnect the fuel manifold and the centerbody.
    Type: Grant
    Filed: December 7, 2016
    Date of Patent: October 19, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Zhongtao Dai, Lance L. Smith, Jeffrey M. Cohen
  • Fuel delivery system having a fuel oxygen reduction unit
    Patent number: 11148824
    Abstract: A fuel system for an aircraft includes a fuel source and a fuel oxygen reduction unit defining a liquid fuel supply path, a stripping gas supply path, a liquid fuel outlet path, and a stripping gas return path, wherein the stripping gas return path and stripping gas supply path are each in airflow communication with the fuel source.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: October 19, 2021
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Brandon Wayne Miller
  • Combustor and gas turbine
    Patent number: 11143404
    Abstract: There is provided a combustor including a nozzle main body (16) that includes a shaft body (24) which extends along an axis and has, inside the shaft body (24), a purge air flow path (29), which extends along the axis to a tip portion of the shaft body (24) and into which compressed air is introduced, and an air spraying hole (39), which is formed in the tip portion of the shaft body (24) and connects the purge air flow path (29) to an outer surface of the shaft body (24), a swirling blade (26), which overhangs from an outer circumferential surface of the shaft body (24) in a diameter direction of the axis and swirls a fluid flowing to a downstream side of an axial direction around the axis, and a fuel spraying hole (38), and a sealing member (40) that seals the air spraying hole (39) and is formed of a metal having a melting point lower than a melting point of a metal forming the nozzle main body (16).
    Type: Grant
    Filed: March 30, 2017
    Date of Patent: October 12, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Taehwan Kim, Keijiro Saito, Shinji Akamatsu, Kenji Miyamoto
  • Combustor and gas turbine including the same
    Patent number: 11143405
    Abstract: The combustor includes a nozzle casing, and combustion nozzles disposed at position spaced apart from each other in the nozzle casing and configured to mix fuel with compressed air and eject the mixture, Where each of the combustion nozzles includes, a nozzle shroud including an inlet through which the compressed air is drawn into the nozzle shroud, and an outlet through which the compressed air is discharged out of the nozzle shroud, an injection cylinder disposed in the nozzle shroud and configured to allow the fuel to be injected into the injection cylinder, and swirlers disposed on an outer circumferential surface of the injection cylinder, where the nozzle shroud includes a region having a constant diameter from the inlet to a predetermined distance along a longitudinal direction of the nozzle shroud.
    Type: Grant
    Filed: October 17, 2018
    Date of Patent: October 12, 2021
    Inventor: Dongsik Han
  • Dual-mode plug nozzle
    Patent number: 11143052
    Abstract: A method for controlling flow through an exhaust nozzle includes: providing a centerbody including a maximum diameter section; providing an inner shroud surrounding the centerbody, including at least a middle section of decreased diameter and terminating at an aft edge; providing an outer shroud. wherein the centerbody and the inner shroud collectively define a throat, and the outer shroud and the centerbody collectively define an exit; selectively translating the inner shroud and outer shroud to vary the throat; and selectively translating the outer shroud to vary the ratio of the exit to the throat; wherein, when the inner shroud is in a forward position, its aft edge is forward of the maximum diameter section of the centerbody, such that the throat of the nozzle is formed between the aft edge of the inner shroud and the centerbody.
    Type: Grant
    Filed: February 5, 2019
    Date of Patent: October 12, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Trevor Andrew Tersmette, Jason Adam Lee
  • Effervescent atomizing structure and method of operation for rotating detonation propulsion system
    Patent number: 11131461
    Abstract: A method and system of effervescent atomization of liquid fuel for a rotating detonation combustor (RDC) for a propulsion system is provided. The method includes flowing liquid fuel through a fuel injection port of a nozzle assembly of the RDC system; flowing a gas through the fuel injection port of the nozzle assembly volumetrically proportional to the liquid fuel; producing a gas-liquid fuel mixture at the fuel injection port by mixing the flow of gas and the flow of liquid fuel; flowing an oxidizer through a nozzle flowpath of the RDC system; producing an oxidizer-gas-liquid fuel mixture by mixing the gas-liquid fuel mixture and the flow of oxidizer within the nozzle flowpath; and igniting the oxidizer-gas-liquid fuel mixture within a combustion chamber of the RDC system.
    Type: Grant
    Filed: December 2, 2019
    Date of Patent: September 28, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sibtosh Pal, Joseph Zelina, Arthur Wesley Johnson, Clayton Stuart Cooper, Steven Clayton Vise
  • System and method for estimation of gas fuel lower heating value using energy balances and parametric error modeling
    Patent number: 11131251
    Abstract: Systems and methods for improved gas turbine engine performance are disclosed. The method can include receiving an error function for a wide range of fuels. The error function can provide lower heating value (LHV) corrections over the wide range of fuels. The method can include receiving gas turbine engine operation data for a first period of run time on the gas turbine from one or more sensors of the gas turbine engine. The engine operation data can include a performance data points. The method can include determining an optimum LHV based on the engine operation data for the first period of run time and the error function. The method can then include adjusting fuel consumption of the gas turbine engine based on the optimum LHV.
    Type: Grant
    Filed: December 22, 2017
    Date of Patent: September 28, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: Cody Allen, Mauricio de Oliveira
  • Combustor with an air mixer and an air swirler each having slots
    Patent number: 11131459
    Abstract: An air mixer includes an annular body defining a center axis. A plurality of slots are defined in the annular body circumferentially spaced apart from one another. Each slot defines a respective center injection axis extending from an outer surface of the annular body to an inner surface of the annular body. Each respective center injection axis is parallel to a respective plane bisecting the annular body. At least one of the slots is intersected by the respective bisecting plane parallel to its respective center injection axis.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: September 28, 2021
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Lev Alexander Prociw, Jacob Greenfield
  • Bent combustion chamber from a turbine engine
    Patent number: 11125435
    Abstract: A turbine engine combustion chamber including: an outer annular housing; a flame tube connected to the outer housing. The flame tube includes an inner annular wall and an outer annular wall and a second axial outlet portion of the flame tube. The flame tube also includes a chamber base located at the inlet of the flame tube; and a fuel injection system configured to inject fuel into the flame tube via the inlet of the flame tube. The injection system includes an injector axis, and an air manifold to move air towards twists in the injection system. The twists are arranged around an implantation axis. The air manifold includes a circular portion around the injector axis. The circular portion, forms an air inlet of the manifold. The opening places the entering air flow in rotation about the implantation axis.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: September 21, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Guillaume Aurelien Godel, Alain Rene Cayre, Romain Nicolas Lunel, Haris Musaefendic
  • Gas turbine
    Patent number: 11118512
    Abstract: There is provided a gas turbine (1) including a compressor (2) that generates compressed air, a casing (5) into which the compressed air is introduced, a combustor (3) that generates a combustion gas, a turbine (4) that is driven by the combustion gas, a combustor cooling system (6) that has a sub-compressor (62), which is able to be operated independently of the compressor (2), and a heat exchanger (61), which extracts air in the casing (5) and causes the air to exchange heat after the sub-compressor (62) has increased a pressure of the air, and that introduces the air, which has exchanged heat, into a cooling passage (31) of a cylindrical body (30) of the combustor (3), and a combustor air introducing system that extracts air flowing in the combustor cooling system (6) and introduces the air into the combustor (3).
    Type: Grant
    Filed: March 28, 2017
    Date of Patent: September 14, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenji Miyamoto, Satoshi Takiguchi, Masakazu Nose
  • Gas turbine lower heating value methods and systems
    Patent number: 11112118
    Abstract: A control system for a gas turbine includes a controller. The controller includes a processor configured to receive a plurality of signals comprising a temperature signal, a pressure signal, a speed signal, a mass flow signal, or a combination thereof, from sensors disposed in the gas turbine system. The processor is further configured to apply the plurality of signals as input to a heating value model. The processor is also configured to execute the heating value model to derive a heating value for a fuel combusted by the gas turbine system. The processor is additionally configured to control operations of the gas turbine system based on the heating value for the fuel.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: September 7, 2021
    Assignee: General Electric Company
    Inventor: Veronica Elizabeth Vela
  • Fuel nozzle cooling structure
    Patent number: 11112117
    Abstract: A fuel nozzle for a combustor assembly of a heat engine is generally provided. The fuel nozzle defines a fuel nozzle centerline therethrough and a radial direction extended from the nozzle centerline. The fuel nozzle includes a first wall extended along the radial direction. The first wall defines a first cooling passage and a second cooling passage each extended therethrough. The first cooling passage is defined at a first acute angle relative to the nozzle centerline. The second cooling passage is defined at a second acute angle 90 degrees or less relative to the first acute angle.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: September 7, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Nayan Vinodbhai Patel, Ying Huang, Duane Douglas Thomsen
  • Fuel polishing system for test cells
    Patent number: 11105268
    Abstract: Systems and methods for providing an automatic fuel polishing and on-demand fuel delivery for one or more gas turbine engine test cells are provided. The system can have a polishing loop that can continuously polish fuel. The polishing loop can have at least a fuel storage tank, a pump assembly, a filtration system, and a flow meter. The system can also have fuel delivery path coupled to the polishing loop at a three way junction. The three way junction can enable the continuous polishing loop when no test cells are operating. Upon initiation of one or more test cells, the delivery path can draw fuel from the polishing loop via the three way junction for use by the test cells. The flow meter can measure a corresponding drop in flow within the polishing loop and cause an increase in flow by the pump assembly.
    Type: Grant
    Filed: May 3, 2018
    Date of Patent: August 31, 2021
    Assignee: Solar Turbines Incorporated
    Inventor: Xing Ouyang
  • Tunable resonator
    Patent number: 11092078
    Abstract: The gas turbine engine includes a fluid system fluidly connecting at least two components of the gas turbine engine, and a tunable resonator in fluid flow communication with the fluid system. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.
    Type: Grant
    Filed: November 28, 2018
    Date of Patent: August 17, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ninad Joshi, Sid-Ali Meslioui
  • Gas turbine and gas turbine operating method
    Patent number: 11085324
    Abstract: A gas turbine is provided with an exhaust diffuser in which an exhaust flow path for circulating exhaust gas from a turbine is formed, and a cooling device for cooling a structure facing the exhaust flow path in the exhaust diffuser. The cooling device has a guide part in which a guide flow path for circulating a cooling medium is formed and which is configured to guide the cooling medium to the structure, and a switching part able to switch between a first state where a flow rate of the cooling medium flowing through the guide flow path is a first flow rate corresponding to a flow rate during a rated operation and a second state where the flow rate of the cooling medium is a second flow rate higher than the first flow rate.
    Type: Grant
    Filed: August 4, 2016
    Date of Patent: August 10, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Takayoshi Iijima, Shinya Hashimoto
  • Variable pitch fan actuator
    Patent number: 11085310
    Abstract: A gas turbine engine including a core having in serial flow order a compressor, a combustor, and a turbine—the compressor, combustor, and turbine together defining a core air flowpath. The gas turbine engine additionally includes a fan section mechanically coupled to the core, the fan section including a plurality of fan blades, and each of the plurality fan blades defining a pitch axis. An actuation device is operable with the plurality fan blades for rotating the plurality fan blades about their respective pitch axes, the actuation device including an actuator located outward of the core air flowpath to, e.g., simplify the gas turbine engine.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: August 10, 2021
    Assignee: General Electric Company
    Inventors: Daniel Alan Niergarth, Darek Tomasz Zatorski, Brandon Wayne Miller