Unitary Injector Having Plural Fuel Flow Paths Patents (Class 60/742)
  • Patent number: 10436447
    Abstract: An augmentor vane assembly of a gas turbine engine with an additively manufactured augmentor vane, the additively manufactured augmentor vane having a vane wall with integral longitudinal wall passages formed therein, at least one of the integral longitudinal wall passages including at least one entrance aperture and at least one exit aperture, the at least one exit aperture transverse to the integral longitudinal wall passage.
    Type: Grant
    Filed: August 1, 2016
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Javier N. Johnson, Chris Bates, Eric Beach, Jorge I. Farah
  • Patent number: 10415833
    Abstract: A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.
    Type: Grant
    Filed: February 16, 2017
    Date of Patent: September 17, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Sravan Kumar Dheeraj Kapilavai, Jin Yan, Anthony John Dean
  • Patent number: 10352570
    Abstract: A fuel injection system for use in a combustor of a turbine engine includes a mixer assembly including a mixer housing and a fuel nozzle assembly positioned radially inward of the mixer housing. The fuel nozzle assembly includes a substantially annular fuel injection housing and a substantially annular main fuel injector coupled to the fuel injection housing. The main fuel injector includes a body, a fuel delivery passage defined in the body, a swirl chamber defined in the body downstream of the fuel delivery passage, and a plurality of circumferentially-spaced fuel metering slots defined in the body and coupled in flow communication with and between the fuel delivery passage and the swirl chamber.
    Type: Grant
    Filed: March 31, 2016
    Date of Patent: July 16, 2019
    Assignee: General Electric Company
    Inventors: Krishnakumar Venkatesan, Michael Anthony Benjamin, Shih-Yang Hsieh, Yuxin Zhang, Owen James Sullivan Rickey, Nayan Vinodbhai Patel, Duane Douglas Thomsen, Kevin Vandevoorde
  • Patent number: 10323575
    Abstract: The invention concerns a gas turbine fuel pipe, having a fuel line, the fuel line having a fuel line volume, a fuel line outer wall and an opening in the fuel line outer wall, a damper having a damper volume and a damper outer wall and attached in fluid communication with the fuel line, wherein the damper covers the opening in the fuel line outer wall, and a perforated lining extending across at least part of the opening in the fuel line outer wall.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: June 18, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Anders Martin Axel Wickström, Devis Tonon, Mirko Ruben Bothien
  • Patent number: 10267522
    Abstract: The present invention relation to a burner for a combustion chamber of a gas turbine with a mixing and injection device. The mixing and injection device includes a limiting wall that defines a gas-flow channel and at least two streamlined bodies, each extending in a first transverse direction into the gas-flow channel. Each streamlined body has two lateral surfaces that are arranged essentially parallel to the main-flow direction, the lateral surfaces being joined to one another at their upstream side to form a leading edge of the body and joined at their downstream side to form a trailing edge of the body. Each streamlined body has a cross-section perpendicular to the first transverse direction that is shaped as a streamlined profile.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: April 23, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Andrea Ciani, John Philip Wood, Douglas Anthony Pennell, Ewald Freitag, Urs Benz, Andre Theuer
  • Patent number: 10152834
    Abstract: A method of conducting prognosis for an airflow management system for a combustion engine includes adjusting a throttle body valve position control signal in response to a detected airflow variation and monitoring an airflow variation compensation (AVC) value corresponding to a degree of adjustment of the control signal. The method also includes generating a throttle body coking severity metric based on at least a plurality of residual error values and the AVC value, and executing at least one response action based on the throttle body coking severity metric exceeding a predetermined threshold.
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: December 11, 2018
    Assignee: GM Global Technology Operations LLC
    Inventors: Chaitanya Sankavaram, Shiming Duan, Layne Wiggins, Stephen Levijoki, Dean Sorrell, Todar Kuzmanov
  • Patent number: 10072848
    Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: September 11, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Jonathan Dwight Berry, Michael John Hughes, Kara Johnston Edwards
  • Patent number: 9885481
    Abstract: The invention refers to a sequential combustor arrangement including a first burner, a first combustion chamber, a dilution burner for admixing a dilution gas and a second fuel via a dilution-gas-fuel-admixer to the first combustor combustion products. The dilution-gas-fuel-admixer has at least one streamlined body which is arranged in the dilution burner for introducing the at least one second fuel into the dilution burner through at least one fuel nozzle, and which has a streamlined cross-sectional profile and which extends with a longitudinal direction perpendicularly or at an inclination to a main flow direction prevailing in the dilution burner. The streamlined body includes a dilution gas opening for admixing dilution gas into the first combustor combustion products upstream of the at least one fuel nozzle. The disclosure further refers to a method for operating a gas turbine with such a sequential combustor arrangement.
    Type: Grant
    Filed: July 29, 2014
    Date of Patent: February 6, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventor: Michael Duesing
  • Patent number: 9851098
    Abstract: The inventive concept relates to a swirler. According to an aspect of the inventive concept, there is provided a swirler including a casing, a pilot body disposed in the casing, and a plurality of vanes arranged along a circumference of the pilot body, wherein at least a part of the vane protrudes further to a downstream than an end portion of the pilot body.
    Type: Grant
    Filed: April 2, 2014
    Date of Patent: December 26, 2017
    Assignee: Hanwha Techwin Co., Ltd.
    Inventor: Ik Soo Kim
  • Patent number: 9605594
    Abstract: A fuel injection device for an annular combustion chamber of a turbine engine, the device including a pilot circuit feeding an injector, a multipoint circuit feeding injection orifices formed in a front face of an annular chamber, and an annular ring mounted in the annular chamber and including fuel-passing orifices opening out into the injection orifices, each fuel-passing orifice formed in the annular ring including a zone of small section that is extended at least downstream or upstream by an orifice portion of increasing section.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: March 28, 2017
    Assignee: SNECMA
    Inventors: Thierry Cortes, Laurent Bernard Cameriano
  • Patent number: 9464808
    Abstract: A nozzle tip assembly and method characterized by the use of a retention device including at least one tab that cooperates with a ledge for coupling a nozzle shroud to a nozzle adaptor. The retention device can be used as a secondary retention feature to prevent nozzle separation and/or to enable the fuel injector to be repaired without having to replace the entire assembly. The latter advantage is of particular benefit when there is damage during assembly or when the nozzle tip assembly is being overhauled.
    Type: Grant
    Filed: November 5, 2009
    Date of Patent: October 11, 2016
    Assignee: Parker-Hannifin Corporation
    Inventors: Stephen C. Paskevich, Bryan T. Runkle, Curtis F. Harding, Jeffrey R. Lehtinen, Jie Qian, Fady Bishara
  • Patent number: 9441835
    Abstract: A system includes a gas turbine combustor configured to combust a fuel and an oxidant, such as O2 and O2 mixtures. The system also includes an aerodynamic peg disposed in the gas turbine combustor. The aerodynamic peg includes a first passage configured to convey a first fluid into the gas turbine combustor and a second passage configured to convey a second fluid into the gas turbine combustor. The first fluid and second fluid are different from one another.
    Type: Grant
    Filed: October 8, 2012
    Date of Patent: September 13, 2016
    Assignee: General Electric Company
    Inventors: Brandon Taylor Overby, David Leach
  • Patent number: 9435540
    Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: September 6, 2016
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Michael John Hughes, Kara Johnston Edwards
  • Patent number: 9435538
    Abstract: The present invention relates to an annular combustion chamber of a gas turbine with—relative to the engine axis—a radially outer combustion chamber wall and a radially inner combustion chamber wall, with the combustion chamber walls forming an annular combustion space, with a combustion chamber head having a plurality of fuel nozzles and air inlet openings, with the respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular and radially outer area and an annular and radially inner area, with the radially outer area and the radially inner area having the same volumes.
    Type: Grant
    Filed: January 22, 2013
    Date of Patent: September 6, 2016
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Carsten Clemen
  • Patent number: 9273868
    Abstract: A system for supporting bundled tube segments within a combustor includes an annular sleeve that extends circumferentially and axially within the combustor, a support lug that extends radially inward from the annular sleeve and an annular support frame that is disposed within the annular sleeve. The annular support frame includes an inner ring portion, an outer ring portion and a plurality of spokes that extend radially between the inner and outer ring portions. The inner ring portion, the outer ring portion and the plurality of spokes define an annular array of openings for receiving a respective bundled tube segment. The inner ring portion is connected to each bundled tube segment and the outer ring portion is coupled to the support lug.
    Type: Grant
    Filed: August 6, 2013
    Date of Patent: March 1, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Patrick Benedict Melton
  • Patent number: 9212609
    Abstract: When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air. The atomized pilot liquid fuel may then be combusted.
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: December 15, 2015
    Assignee: Solar Turbines Incoporated
    Inventors: Christopher Zdzislaw Twardochleb, Robert Anthony Corr, II
  • Patent number: 9181812
    Abstract: A combustion device used in gas turbine engines to produce propulsion or rotate a shaft for power generation includes a can-annular combustor with a system of fuel and air inlet passages and nozzles that results in an optimal combustion environment of premixed fuel and air. The fuel-air inlets are placed at various longitudinal locations and circumferentially distributed, and direct the flow tangentially or nearly tangent to the can liner. The combustion device provides effective mixing of fuel and air, creates an environment for combustion that reduces pollutant emissions, reduces the need for costly pollution control devices, enhances ignition and flame stability, reduces piloting issues, and improves vibration reduction.
    Type: Grant
    Filed: May 3, 2010
    Date of Patent: November 10, 2015
    Inventors: Majed Toqan, Brent Allan Gregory, Jonathan David Regele, Ryan Sadao Yamane
  • Patent number: 9115899
    Abstract: A gas turbine combustor stably burns low-BTU gases, such as blast furnace gases, that are heavily laden with CO2. The gas turbine combustor includes a double-swirling burner with an inner swirler and an outer swirler, the burner having a configuration with gas fuel injection holes and air injection holes arranged at alternate positions in the inner swirler and with gas injection holes arranged in the outer swirler. In addition, fuel injection holes for enhancing flame stability are provided at positions radially inward of the inner swirler. An inner flame by the inner swirler and an outer flame by the outer swirler interact with each other to stably burn the low-BTU gas. In the inner swirler, the gas injection holes and air injection holes arranged at alternate positions contributes to raising a temperature of the inner flame to a level required for flame stabilization.
    Type: Grant
    Filed: February 15, 2013
    Date of Patent: August 25, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Hiromi Koizumi, Shohei Yoshida, Satoshi Dodo
  • Patent number: 9046272
    Abstract: A combustor liner assembly support is provided that is used to axially and radially position combustor liners in a gas turbine engine. The combustor liner support includes, in one embodiment, a support bracket that is coupled to a diffuser located upstream in the gas turbine engine; a support spool coupled to the support bracket; and a mount stake coupled to the support spool. The mount stake is connected to the combustor liners and maintains the spaced relation therebetween. An alignment device can be used between the support bracket and the support spool.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: June 2, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Edward Claude Rice
  • Patent number: 9032736
    Abstract: A method for operating a burner comprising a burner axis and at least one jet nozzle is provided. The nozzle or nozzles include a central axis, a jet nozzle outlet, a wall that runs in a radial direction starting from the central axis and that faces the burner axis and a volumetric fluid flow that includes a fuel and flows through the jet nozzle or nozzles to the jet nozzle outlet. An air film is formed at the jet nozzle outlet between the volumetric fluid flow including the fuel and the wall that faces the burner axis by means of air that is injected into the jet nozzle or nozzles along the wall that faces the burner axis.
    Type: Grant
    Filed: March 16, 2010
    Date of Patent: May 19, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Matthias Hase
  • Patent number: 9032703
    Abstract: In a gas turbine engine that includes a compressor and a combustor, wherein the combustor includes a primary fuel injector within a fuel nozzle and a secondary fuel injector that is upstream of the fuel nozzle and configured to inject fuel into a flow annulus of the combustor, a method for detecting a flame holding condition about a fuel injector. The method may include the steps of: detecting an upstream pressure upstream of the secondary fuel injector; detecting a downstream pressure downstream of the secondary fuel injector; determining a measured pressure difference between the upstream pressure and the downstream pressure; and comparing the measured pressure difference to an expected pressure difference.
    Type: Grant
    Filed: June 20, 2011
    Date of Patent: May 19, 2015
    Assignee: General Electric Company
    Inventors: Anthony Wayne Krull, Gilbert Otto Kraemer, Garth Curtis Frederick, David Kaylor Toronto
  • Patent number: 9027349
    Abstract: A combustor of the prior art that defines the outlet position and direction of an air hole and suppresses adhesion of flame to an air hole outlet can reduce a discharge amount of NOx by increasing a distance over which fuel and air are mixed with each other. However, such a combustor is not sufficiently discussed for measures to suppress the occurrence of combustion oscillation resulting from the variation of a flame surface. A combustor 2 according to the present invention includes a combustion chamber 5 to which fuel and air are supplied; air holes 32 adapted to supply air to the combustion chamber 5; fuel nozzles 25 adapted to supply gaseous fuel to the air holes 32; and orifices 24 adapted to allow the gaseous fuel supplied to the air holes 32 to cause a pressure drop.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: May 12, 2015
    Assignee: Mitsubishi Hitachi Power Systems, Ltd.
    Inventors: Keisuke Miura, Tomomi Koganezawa, Satoshi Dodo, Takeo Saito
  • Patent number: 9021781
    Abstract: A fuel injector for a combustor of a gas turbine includes an annular main body. A fluid circuit extends at least partially through the main body. An axially extending inner body extends within the main body. The inner body at least partially defines an inner chamber that extends at least partially through the inner body. The inner chamber is in fluid communication with the fluid circuit. A retractable igniter extends linearly outward from the inner chamber when the fluid circuit is charged.
    Type: Grant
    Filed: January 4, 2013
    Date of Patent: May 5, 2015
    Assignee: General Electric Company
    Inventors: Kaitlin Marie Graham, James Scott Flanagan, Jeffrey Scott LeBegue
  • Patent number: 8991188
    Abstract: A cooling circuit for a fuel nozzle in a gas turbine includes an end cap cavity receiving passive purge flow from a compressor of the turbine, and fuel nozzle swozzles disposed in a swozzle shroud that impart swirl to incoming fuel and air. Purge slots are formed in the swozzle shroud and through the fuel nozzle swozzles in fluid communication with the end cap cavity. The purge slots are positioned upstream of a quat fuel injection passage, and the passive purge flow enters fuel nozzle tip cavities of the fuel nozzle to provide tip cooling and tip purge volume without mixing the passive purge flow with quat fuel.
    Type: Grant
    Filed: January 5, 2011
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Donald Mark Bailey, Robert Rohrssen
  • Patent number: 8991187
    Abstract: The present application provides for a combustor for combusting a flow of fuel and a flow of air. The combustor may include a number of fuel nozzles, a lean pre-nozzle fuel injection system positioned upstream of the fuel nozzles, and a premixing annulus positioned between the fuel nozzles and the lean pre-nozzle fuel injection system to premix the flow of fuel and the flow of air.
    Type: Grant
    Filed: October 11, 2010
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Michael John Hughes, Jonathan Dwight Berry, Jason Thurman Stewart, Almaz Valeev, Chunyang Wu
  • Patent number: 8973367
    Abstract: Disclosed is a fuel lance for a burner, in particular a gas turbine burner, including a tip that has a nozzle surface including at least two fuel nozzles. The nozzle surface is provided with slots between the fuel nozzles. As a rule, the lance is provided for operation with a liquid fuel.
    Type: Grant
    Filed: November 5, 2009
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Tobias Krieger, Jürgen Meisl
  • Patent number: 8966908
    Abstract: A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to a second end. The first end may be configured to be fluidly coupled to a compressor of the turbine engine and the second end may be configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a perforated plate positioned proximate the first end of the passageway. The perforated plate may be configured to direct compressed air into the annular passageway with a first pressure drop. The fuel injector may also include at least one fuel discharge orifice positioned downstream of the perforated plate. The at least one fuel discharge orifice may be configured to discharge a fuel into the annular passageway with a second pressure drop.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: March 3, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: Christopher Zdzislaw Twardochleb, Hongyu Wang, James Wilfrid Blust, Mario E. Abreu
  • Patent number: 8966907
    Abstract: Present embodiments are directed toward reducing low flow or no flow situations in a head end of a turbine combustor. Embodiments include a system having a turbine combustor. The turbine combustor includes a fuel nozzle having an inner shell and an outer shell, and a feed cap disposed about the fuel nozzle and having an outer wall and a back plate. The back plate joins respective upstream ends of the outer shell of the fuel nozzle and the outer wall of the feed cap. The turbine combustor is configured to flow a first pressurized air via an air path extending along the outer wall of the feed cap, the back plate of the feed cap, and into the fuel nozzle.
    Type: Grant
    Filed: April 16, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Abdul Rafey Khan, Bradley Donald Crawley, Robert Joseph Rohrssen, Mohan Krishna Bobba
  • Patent number: 8966909
    Abstract: A system and method for reducing combustion dynamics includes first and second combustors arranged about an axis, and each combustor includes a plurality of tubes that extend axially through at least a portion of the combustor and a combustion chamber downstream from the plurality of tubes. A fuel injector extends through each tube to provide fluid communication into each tube at a fourth axial distance from the combustion chamber. The fourth axial distance in the first combustor is different than the fourth axial distance in the second combustor.
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Sarah Lori Crothers, Gilbert Otto Kraemer
  • Patent number: 8959923
    Abstract: An arrangement for preparation of a fuel for combustion including a burner is provided. The arrangement includes a combustion chamber associated with the burner and in which combustion of a fuel is to take place, as well as means for supplying liquid fuel to the arrangement through an internal passage in the burner for the combustion, solid portions of the burner body being heated by the combustion, wherein the internal passage is located inside the solid portions of the burner body for receiving heat energy evaporating the fuel from these body portions, and that it includes means for conveying vaporized fuel to the combustion chamber to take part in the combustion.
    Type: Grant
    Filed: February 20, 2012
    Date of Patent: February 24, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ulf Nilsson, Peter Senior
  • Patent number: 8959772
    Abstract: A multipoint injector for a turbomachine according to which any risk of fuel coking is eliminated is disclosed. The multipoint fuel which is liable to stagnate inside the circuit thereof is cooled uniformly, due to the formation of continuous baffles which each communicate with at least one separate circulation channel and of which the peripheral baffles open out into a fuel admission chamber arranged in a zone diametrically opposing the circulation channels and which communicates with the injection nozzle for pilot fuel in order to achieve uniform supply and cooling of the injector.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: February 24, 2015
    Assignee: SNECMA
    Inventors: Didier Hippolyte Hernandez, Thomas Olivier Marie Noel
  • Patent number: 8955328
    Abstract: A burner arrangement is provided. The burner arrangement includes a support and at least two fuel nozzles attached to the support in the direction of flow, with each fuel nozzle including a support-side section which includes a contact surface on the support side with which it rests on a supporting surface of the support, with at least two fuel nozzle tips embodied in one piece extending out from the support-side section in the direction of flow and the support-side contact surface including at least two extension parts projecting in the direction of the support, with the extension parts each embodying a channel through which fuel is fed in each case to the fuel nozzle tips through passages which are arranged in the support-side contact surface of the support-side section.
    Type: Grant
    Filed: February 17, 2011
    Date of Patent: February 17, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Timothy A. Fox, Thomas Grieb, Tobias Krieger, Stephen A. Ramier
  • Patent number: 8955329
    Abstract: A fuel nozzle assembly has been conceived for a combustor in a gas turbine including a first passage and fourth passage connectable to a source of gaseous fuel, a second passage connectable to a source of a gaseous oxidizer, and a third passage coupled to a source of a diluent gas, wherein the first passage is a center passage and is configured to discharge gaseous fuel from nozzles at a discharge end of the center passage, the second passage is configured to discharge the gaseous oxidizer through nozzles adjacent to the nozzles for the center passage, the third passage discharges a diluent gas through nozzles adjacent to the nozzles for the second passage, and the fourth passage is configured to discharges the gaseous fuel downstream of the discharge location for the first, second and third passages.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: February 17, 2015
    Assignee: General Electric Company
    Inventors: Predrag Popovic, Abinash Baruah
  • Patent number: 8938968
    Abstract: An exemplary burner of a gas turbine includes a tubular body with an inlet for an entrance of an air flow, downstream of inlet vortex generators, and a lance projecting into the tubular body and having a terminal portion extending along a longitudinal axis of the burner which is provided with nozzle groups for injecting fuel into the tubular body. The nozzle groups can lay in an injection plane perpendicular to the axis of the terminal portion of the lance. Downstream of the lance, the burner has an outlet. A ratio x/L between an axial distance x between the side trailing edge of the vortex generator and the injection plane, and the length L of the tubular body can be less than approximately 0.1052.
    Type: Grant
    Filed: December 18, 2009
    Date of Patent: January 27, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Johannes Buss, Andrea Ciani, Michael Düsing, Adnan Eroglu
  • Patent number: 8925325
    Abstract: Combustion systems and the related methods operate to supply a stream of combustion products to a turbine in a gas turbine engine by forming an outer recirculation zone of recirculating combustion products within a combustor and by forming an inner recirculation zone inboard of the outer recirculation zone. The inner and outer recirculation zones are formed by imparting swirl to compressor discharge air passing through an outer air swirler and an inner air swirler radially inboard of the outer air swirler. Fuel is injected from an outer fuel injector into the outer recirculation zone, and fuel is also injected from an inner fuel injector into the inner recirculation zone.
    Type: Grant
    Filed: April 8, 2011
    Date of Patent: January 6, 2015
    Assignee: Delavan Inc.
    Inventors: Nicholas R. Overman, John Earl Short
  • Patent number: 8925323
    Abstract: A system includes a fuel nozzle. The fuel nozzle includes a center body configured to receive a first portion of air and to deliver the air to a combustion region. The fuel nozzle also includes a swirler configured to receive a second portion of air and to deliver the air to the combustion region. The swirler includes an outer shroud wall, an inner hub wall, and a swirl vane. The swirl vane includes a radial swirl profile at a downstream edge of the swirl vane. The radial swirl profile includes a region extending from the outer shroud wall to a first transition point and a second region extending from the transition point to the inner hub wall. At least one of the first and second regions is substantially straight and at least one of the first and second regions is arcuate.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: January 6, 2015
    Assignee: General Electric Company
    Inventor: Baifang Zuo
  • Patent number: 8925324
    Abstract: A turbomachine includes a compressor section, a combustor operatively connected to the compressor section, an end cover mounted to the combustor, and an injection nozzle assembly operatively connected to the combustor. The injection nozzle assembly includes a plurality of mixing tube elements. Each of the plurality of mixing tube elements includes a conduit having a first fluid inlet, a second fluid inlet arranged downstream from the first fluid inlet, a discharge end arranged downstream from the first and second fluid inlets, and a vortex generator arranged between the first and second fluid inlets. The vortex generator is configured and disposed to create multiple vortices within the conduit to mix first and second fluids passing through each of the plurality of mixing tube elements.
    Type: Grant
    Filed: October 5, 2010
    Date of Patent: January 6, 2015
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Chunyang Wu, Baifang Zuo
  • Publication number: 20150000286
    Abstract: A combustor includes an end cover having an outer side and an inner side, an outer barrel having a forward end that is adjacent to the inner side of the end cover and an aft end that is axially spaced from the forward end. An inner barrel is at least partially disposed concentrically within the outer barrel and is fixedly connected to the outer barrel. A fluid conduit extends downstream from the end cover. A first bundled tube fuel injector segment is disposed concentrically within the inner barrel. The bundled tube fuel injector segment includes a fuel plenum that is in fluid communication with the fluid conduit and a plurality of parallel tubes that extend axially through the fuel plenum. The bundled tube fuel injector segment is fixedly connected to the inner barrel.
    Type: Application
    Filed: July 1, 2013
    Publication date: January 1, 2015
    Inventors: Jeffrey Scott LeBegue, Patrick Benedict Melton, James Harold Westmoreland, III, James Scott Flanagan
  • Patent number: 8919127
    Abstract: A system includes a gas turbine combustor, which includes a combustion liner disposed about a combustion region, a flow sleeve disposed about the combustion liner, an air passage between the combustion liner and the flow sleeve, and a structure between the combustion liner and the flow sleeve. The structure obstructs an airflow through the air passage. The gas turbine combustor also includes a wake reducer disposed adjacent the structure. The wake reducer directs a flow into a wake region downstream of the structure.
    Type: Grant
    Filed: May 24, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Patrick Benedict Melton, Ronald James Chila, Abdul Rafey Khan, Carolyn Ashley Antoniono
  • Patent number: 8919673
    Abstract: A fuel nozzle includes a fuel plenum, an outer body surrounding the fuel plenum, and bore holes that extend longitudinally through the outer body. The fuel nozzle also includes means for fixedly attaching the fuel plenum to the outer body and passages that provide fluid communication between the fuel plenum and the bore holes. A method for manufacturing a fuel nozzle includes drilling bore holes longitudinally through an outer body and drilling passages in the outer body to the bore holes. The method further includes inserting a fuel plenum into the outer body, wherein the passages provide a fluid communication between the bore holes and the fuel plenum, and attaching the fuel plenum to the outer body.
    Type: Grant
    Filed: April 14, 2010
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Karthik Subramanian, Bryan Wesley Romig
  • Patent number: 8904800
    Abstract: A combustor dome heat shield and a louver are separately metal injection molded and then fused together to form a one-piece combustor heat shield.
    Type: Grant
    Filed: October 10, 2012
    Date of Patent: December 9, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Lorin Markarian, Melissa Despres
  • Patent number: 8899049
    Abstract: A system is disclosed that includes a combustor having an end cover and at least one fuel nozzle assembly extending from an inner face of the end cover. A cartridge may extend through the end cover and into the fuel nozzle assembly. The cartridge may define an opening for receiving light emitted from within the combustor. Additionally, a fiber optic cable may be disposed within the cartridge and may be configured to capture at least a portion of the light received through the opening.
    Type: Grant
    Filed: January 7, 2011
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Anthony Wayne Krull, Nan Zong, Danielle Marie Kalitan
  • Patent number: 8893500
    Abstract: A dual fuel injector for a gas turbine engine includes a central cavity extending along a longitudinal axis from a first end to a second end, and a first fuel discharge outlet configured to direct a first fuel into the central cavity at the first end. The fuel injector may also include a first air discharge opening circumferentially disposed about the first fuel discharge outlet and configured to direct a first quantity of air into the central cavity, and a second air discharge opening circumferentially disposed about the central cavity and configured to discharge a second quantity of air into the central cavity downstream of the first air discharge outlet. The fuel injector may further include a second fuel discharge outlet circumferentially disposed about the central cavity and configured to discharge a second fuel therethrough. The second fuel may be different from the first fuel.
    Type: Grant
    Filed: May 18, 2011
    Date of Patent: November 25, 2014
    Assignee: Solar Turbines Inc.
    Inventor: Gareth W. Oskam
  • Publication number: 20140318137
    Abstract: A fuel nozzle apparatus includes: a fuel distributor including an annular distributor ring, an aft interior mounting surface; and a pilot supply tube; a venturi defining a splitter with a first bore, and axially spaced-apart forward and aft exterior mounting surfaces; and a swirler including second bore and a forward interior mounting surface. The pilot supply tube is received in the second bore, outer ends of the inner vanes are received in the first bore; and the forward and aft exterior mounting surfaces of the venturi are received in the forward and aft interior mounting surfaces, respectively.
    Type: Application
    Filed: July 10, 2014
    Publication date: October 30, 2014
    Inventors: Marie Ann McMasters, Michael A. Benjamin, Alfred Mancini, Steven Joseph Lohmueller
  • Patent number: 8869534
    Abstract: A burner for a gas turbine including a main burner and a pilot burner is provided. The main burner has a supporting structure, a heat shield and a holder for the heat shield, and wherein the holder is at least partially located within the supporting structure and the heat shield is at least partially located within the holder. The heat shield is fastened to the holder by a force-fit and/or a frictional connection.
    Type: Grant
    Filed: December 20, 2007
    Date of Patent: October 28, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Andreas Böttcher, Thomas Grieb, Jens Kleinfeld, Tobias Krieger, Sabine Tüschen, Ulrich Wörz
  • Patent number: 8850821
    Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple first fuel outlets disposed on the hub, and multiple swirl vanes disposed in the airflow path downstream from the multiple first fuel outlets.
    Type: Grant
    Filed: October 7, 2011
    Date of Patent: October 7, 2014
    Assignee: General Electric Company
    Inventors: Abdul Rafey Khan, Bradley Donald Crawley, Donald Mark Bailey, Ajay Pratap Singh
  • Patent number: 8850822
    Abstract: A system includes a fuel nozzle. The fuel nozzle includes a hub having an axis, a shroud disposed about the hub, an airflow path between the hub and the shroud, multiple vanes extending between the hub and the shroud, and a first fuel path leading to multiple first fuel outlets disposed on the multiple vanes. The fuel nozzle also includes a second fuel path leading to multiple second fuel outlets disposed on at least one of the hub and/or the shroud, wherein the multiple second fuel outlets are disposed at an axial distance upstream from a downstream end of the hub.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: October 7, 2014
    Assignee: General Electric Company
    Inventors: Nishant Govindbhai Parsania, Ajay Pratap Singh
  • Publication number: 20140283524
    Abstract: A fuel nozzle system for enabling a gas turbine to start and operate on low-Btu fuel includes a primary tip having primary fuel orifices and a primary fuel passage in fluid communication with the primary fuel orifices, and a fuel circuit capable of controlling flow rates of a first and second low-Btu fuel gases flowing into the fuel nozzle. The system is capable of operating at an ignition status, in which at least the first low-Btu fuel gas is fed to the primary fuel orifices and ignited to start the gas turbine, and a baseload status, in which at least the second low-Btu fuel gas is fired at baseload. The low-Btu fuel gas ignited at the ignition status has a content of the first low-Btu fuel gas higher than that of the low-Btu fuel gas fired at the baseload status. Methods for using the system are also provided.
    Type: Application
    Filed: January 14, 2014
    Publication date: September 25, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Suhui LI, Joel Meier HAYNES, Ping YU, Wei Chen, David Leach, John Joseph Lipinski, Manuel Moises Cardenas, JR., Wenjie Wu, Qingguo Zhang
  • Publication number: 20140260302
    Abstract: The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows of gas fuel, a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, a number of swirler gas fuel ports defined in the swirler, and a number of downstream face gas fuel ports defined in the downstream face of the fuel nozzle. The swirler may include a number of swirl vanes and a number of air chambers defined between adjacent swirl vanes. The present application and the resultant patent further provide a method of operating a diffusion combustor fuel nozzle of a gas turbine engine.
    Type: Application
    Filed: March 14, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Arvind Venugopal Menon, Gilbert Otto Kraemer, Predrag Popovic, Abinash Baruah
  • Patent number: 8820087
    Abstract: A method and system for controlling delivery of fuel to a dual stage nozzle in the combustor of a gas turbine. A liquid fuel is conveyed from a single stage fuel supply through a plurality of primary fuel supply lines to a first nozzle stage including a plurality of primary nozzles. A predetermined operating condition of the gas turbine is identified and a signal is produced in response to the identified operating condition. The signal effects actuation of valves located on secondary fuel supply lines extending from each of the primary fuel supply lines to supply fuel to respective secondary nozzles.
    Type: Grant
    Filed: September 8, 2008
    Date of Patent: September 2, 2014
    Assignee: Siemens Energy, Inc.
    Inventor: William R. Ryan