Having Bluff Flame Stabilization Means Patents (Class 60/749)
  • Patent number: 10557633
    Abstract: A combustor according to the present invention is provided with: a pilot burner (15) disposed along an axis (P); a plurality of premixing burners (16), each of which has a premixing swirler cylinder (19) and a premixing nozzle (20) disposed inside the premixing swirler cylinder (19) and that are disposed about the axis (P) in the circumferential direction so as to surround the periphery of the pilot burner (15); a substrate (23) through which the pilot burner (15) and the premixing swirler cylinders (19) are individually inserted so as to be supported therein; and stagnation eliminating blocks (27) that are provided so as to fill spaces between the premixing swirler cylinders (19) on a surface of the substrate (23) on the downstream side, wherein air film supplying ports (38) that form air films A on surfaces of the stagnation eliminating blocks (27) are formed in the stagnation eliminating blocks (27).
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: February 11, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Yusuke Tanaka, Keijiro Saito, Shinji Akamatsu
  • Patent number: 10215416
    Abstract: The burner of a gas turbine has a duct, a vortex generator extending in the duct and including a leading edge and a trailing edge. The trailing edge has a first order lobed shape. The first order lobed shape is defined by a second order lobed shape. Preferably a nozzle for fuel injection is connected to the vortex generator and the second order lobed shape is only provided at the nozzles.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: February 26, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Michael Dusing, Madhavan Narasimhan Poyyapakkam, Stefan Wysocki
  • Patent number: 9713570
    Abstract: A mobile treatment apparatus for use in treating a user of the apparatus with medical or therapeutic gases, comprising a mixing unit for containing water and having a motionless mixing means; a gas cartridge unit removably mounted to the mixing unit via a cartridge piercing module, wherein a pressure-regulating valve regulates a flow rate of a gas from the cartridge through the mixing means, to achieve a specified gas-water mixture that is effective for transdermal delivery of the gas to the user; and a wearable receiver suit for forming a space around at least an area of the user's body to be treated, wherein the suit is connected to the mixing unit, for delivery of the gas to treat the area via the transdermal delivery.
    Type: Grant
    Filed: April 9, 2008
    Date of Patent: July 25, 2017
    Assignee: Respiderm Corporation
    Inventors: Péter Török, József Török, Tamás Török, Karsa Tímea
  • Patent number: 9388742
    Abstract: A swirler inlet valve plate for a fuel injector of a gas turbine engine includes a blocker ring and a pivot sleeve mechanically connected to the blocker ring. The blocker ring is formed from at least a portion of a toroid shape. The blocker ring includes a blocking surface perpendicular to an axis of the blocker ring formed from at least a portion of an annulus. The blocker ring also includes a flow surface, an inner circumferential surface of the toroidal shape. The pivot sleeve includes a sleeve portion extending adjacent the blocker ring. The sleeve portion includes a rotation transmission mechanism.
    Type: Grant
    Filed: May 8, 2013
    Date of Patent: July 12, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Georgina J. McGee, Thomas John Chipman Rogers, Anthony Fahme, Daniel Paul Panayil
  • Patent number: 9347669
    Abstract: The present invention discloses a novel apparatus and method for operating a gas turbine combustor having a structural configuration proximate a pilot region of the combustor which seeks to minimize the onset of thermo acoustic dynamics. The pilot region of the combustor includes a generally cylindrical extension having an outlet end with an irregular profile which incorporates asymmetries into the system so as to destroy any coherent structures.
    Type: Grant
    Filed: September 26, 2013
    Date of Patent: May 24, 2016
    Assignee: ALSTOM TECHNOLOGY LTD.
    Inventors: Peter John Stuttaford, Stephen Jorgensen, Yan Chen, Hany Rizkalla, Khalid Oumejjoud, Mirko R. Bothien
  • Patent number: 9234662
    Abstract: A fuel-air premixer for use in a combustor of a gas turbine includes an air inlet, a fuel inlet, a shroud, a central body and a cascade of vanes. The premixer mixes fuel and air in the annular mixing passage into a uniform mixture for injecting into a combustor reaction zone. The air from a compressor is injected into the mixer through an air inlet. The fuel is introduced into air stream via fuel injection holes that pass through the walls of the vanes which contain internal fuel flow passages. The flow field inside the premixer is broken up by the arrayed vanes into a series of small regions each containing a well designed small size mixing eddy which is steadily attached to the surface of the vanes.
    Type: Grant
    Filed: November 13, 2012
    Date of Patent: January 12, 2016
    Assignee: The Institute of Engineering Thermophysics, The Chinese Academy of Sciences
    Inventors: Yue Wang, Zongming Yu, Wenjun Kong, Baorui Wang, Yuhua Ai
  • Patent number: 9068748
    Abstract: A combustor for a gas turbine engine includes a radially inboard liner, a radially outboard liner, and a bulkhead that cooperatively define an annular combustion chamber, a plurality of first fuel injectors that are disposed in the bulkhead, and a plurality of second fuel injectors that are disposed in at least one of the inboard liner and the outboard liner aftward of the bulkhead. A method is also provided for operating the combustor of the gas turbine engine wherein fuel distribution between the forward combustion zone and the downstream combustion zone is selectively varied in response to the power operating mode of the gas turbine engine with an objective to control NOx formation.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: June 30, 2015
    Assignee: United Technologies Corporation
    Inventor: James B. Hoke
  • Patent number: 9027350
    Abstract: A gas turbine engine including a combustor with a combustion liner having inner and outer walls is disclosed herein. The gas turbine engine further includes a swirler system adapted to receive a fuel injector and a flow splitter operable to bifurcate an airflow exiting the swirler system into a first bifurcated flow and a second bifurcated flow. A shroud is positioned downstream of the flow splitter and is configured to deflect the first bifurcated flow in a first direction radially inward and the second bifurcated flow in a second direction radially outward. The second bifurcated flow cools both of the inner and outer walls of the combustor liner.
    Type: Grant
    Filed: October 26, 2010
    Date of Patent: May 12, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Timothy Carl Roesler
  • Patent number: 9004912
    Abstract: A combustor includes an end cap having an upstream surface axially separated from a downstream surface. A cap shield circumferentially surrounds the upstream and downstream surfaces, tubes extend from the upstream surface through the downstream, and a plenum is inside the end cap. A first baffle extends radially across the plenum toward the cap shield, and a plate extends radially inside the plenum between the first baffle and the upstream surface. A method for supplying fuel to a combustor includes flowing a working fluid through tubes, flowing a fuel into a plenum between upstream and downstream surfaces, radially distributing the fuel along a first baffle, and axially flowing the fuel across a plate that extends radially inside the plenum.
    Type: Grant
    Filed: November 11, 2011
    Date of Patent: April 14, 2015
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Patrick Benedict Melton, James Harold Westmoreland, III
  • Patent number: 8979525
    Abstract: The invention relates to a streamlined body for influencing the flow dynamics of a fluid, wherein the streamlined body at least partly corresponds to a rotationally symmetrical airfoil. A streamlined body of this kind can be used in a number of ways, for example as an impact member, as a flow regulator or as a heat exchanger. It also evens out and accelerates flows. It is used to particular advantage in a mixing and reaction chamber for burning fuels.
    Type: Grant
    Filed: November 25, 2002
    Date of Patent: March 17, 2015
    Assignee: Brambel Trading Internacional LDS
    Inventors: Franz Josef Staffler, Vincenzo Branzi
  • Patent number: 8950189
    Abstract: A fuel injection array for a gas turbine engine includes a plurality of bluff body injectors and a plurality of swirler injectors. A control operates the plurality of bluff body injectors and swirler injectors such that bluff body injectors are utilized without all of the swirler injectors at least at low power operation. The swirler injectors are utilized at higher power operation.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: February 10, 2015
    Assignee: United Technologies Corporation
    Inventor: Timothy S. Snyder
  • 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
  • Publication number: 20140338345
    Abstract: A jet engine flame holder bluffbody is provided that includes a leading edge that is rounded, a mid-body having a rectangular cross-section, and a trailing edge, where the trailing edge includes a rectangular cross-section having digitated cutouts from the rectangular cross-section, where the tailing edge projects upward according to a digitated cross-section, where material digits remain between consecutive pairs of the digitated cutouts.
    Type: Application
    Filed: June 5, 2013
    Publication date: November 20, 2014
    Inventors: Wookyung Kim, Mark Godfrey Mungal, Heinz Guenter Pitsch
  • Patent number: 8863525
    Abstract: The present application provides a combustor. The combustor may include an air flow path with a flow of air therein. A flow obstruction may be positioned within the air flow path and cause a wake or a recirculation zone downstream thereof. A number of fuel injectors may be positioned downstream of the flow obstruction. The fuel injectors may inject a flow of fuel into the air flow path such that the flows of fuel and air in the wake or the recirculation zone do not exceed a flammability limit.
    Type: Grant
    Filed: January 3, 2011
    Date of Patent: October 21, 2014
    Assignee: General Electric Company
    Inventors: David Kaylor Toronto, Kwanwoo Kim, Abdul Rafey Khan, Luis Flamand
  • Patent number: 8800290
    Abstract: A gas turbine engine combustor has inboard and outboard walls. A forward bulkhead extends between the walls and cooperates therewith to define a combustor interior volume. Bluff body fuel injectors are along the bulkhead.
    Type: Grant
    Filed: December 18, 2007
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Steven W. Burd, Stephen K. Kramer, John T. Ols, Albert K. Cheung
  • Patent number: 8769955
    Abstract: A port (60) for axially staging fuel and air into a combustion gas flow path 28 of a turbine combustor (10A). A port enclosure (63) forms an air path through a combustor wall (30). Fuel injectors (64) in the enclosure provide convergent fuel streams (72) that oppose each other, thus converting velocity pressure to static pressure. This forms a flow stagnation zone (74) that acts as a valve on airflow (40, 41) through the port, in which the air outflow (41) is inversely proportion to the fuel flow (25). The fuel flow rate is controlled (65) in proportion to engine load. At high loads, more fuel and less air flow through the port, making more air available to the premixing assemblies (36).
    Type: Grant
    Filed: June 2, 2010
    Date of Patent: July 8, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: William F. Van Nieuwenhuizen, Timothy A. Fox, Steven Williams
  • Patent number: 8707704
    Abstract: A method of assembling a turbine engine includes defining a first chamber and defining a second chamber. The method also includes forming at least one venturi device oriented with a predetermined venturi step angle greater than approximately 48°. The method further includes coupling the first chamber in flow communication with the second chamber via the venturi device therebetween.
    Type: Grant
    Filed: May 31, 2007
    Date of Patent: April 29, 2014
    Assignee: General Electric Company
    Inventors: Derrick Walter Simons, Jeffrey Scott Lebegue, Krishna Kumar Venkataraman
  • Patent number: 8646275
    Abstract: A gas-turbine lean combustor includes a combustion chamber (2) and a fuel nozzle (1) which includes a pilot fuel injection (17) and a main fuel injection (18). The main fuel injection (18) includes central recesses (23) for a controlled inhomogeneous fuel injection, the number of said recesses on the circumference ranging from 8 to 40 and said recesses having an angle of inclination ?2 in circumferential direction of 10°??2?60° and an axial angle of inclination ?1 relative to the combustor axis (4) between ?10°??1?90°.
    Type: Grant
    Filed: March 8, 2012
    Date of Patent: February 11, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Leif Rackwitz, Imon-Kalyan Bagchi, Thomas Doerr
  • Publication number: 20130213050
    Abstract: A recuperated micro gas turbine combustor has a casing, liner, fuel injector and a flame stabilization device. This flame stabilization device is characterized by a swirl strength and air passage geometry as such that the pressure loss over the device is less than 1.5%. The flame stabilization device and the fuel injector form together with the liner inlet/head hardware a single burner.
    Type: Application
    Filed: March 21, 2013
    Publication date: August 22, 2013
    Applicant: Miro Turbine Technology BV
    Inventor: Micro Turbine Technology BV
  • Patent number: 8454350
    Abstract: Disclosed is a combustor including a baffle plate having at least one through baffle hole and at least one fuel nozzle extending through the at least one through baffle hole. At least one diluent shroud is affixed to the at least one baffle plate and is configured to guide a diluent flow toward a mixing chamber of the at least one fuel nozzle. Further disclosed is a method for introducing a diluent flow into a mixing chamber of a fuel nozzle including urging the diluent flow from a plenum through a baffle plate gap between a baffle plate and an outer surface of the fuel nozzle. The diluent flow is directed via at least one diluent shroud extending from the baffle plate toward a plurality of air swirler holes extending through a fuel nozzle tip. The diluent flow is flowed through the plurality of air swirler holes into the mixing chamber.
    Type: Grant
    Filed: October 29, 2008
    Date of Patent: June 4, 2013
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, John Joseph Lipinski, Girard Albert Simons, Abhijit Som
  • Patent number: 8327643
    Abstract: A main swirler of a triple annular configuration that is partitioned by a pre-filmer and a separator is installed in an inlet port of a main air flow channel. The vicinity of the inner wall of the main air flow channel provided with a main fuel injection port is bulged radially outward from the innermost surface (innermost surface of a small swirler) of a main swirler. Further, a distance from the main fuel injection port and the pre-filmer is set such that an effective opening area between the pre-filmer and “the inner wall of the main air flow channel provided with the main fuel injection port” is equal to an effective opening area of the small swirler. The swirling directions of the swirlers of the main swirler are “clockwise”-“counter-clockwise”-“clockwise” respectively along the radial outward direction when the swirling direction of the innermost swirler is taken as “clockwise”.
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: December 11, 2012
    Assignee: Japan Aerospace Exploration Agency
    Inventors: Takeshi Yamamoto, Kazuo Shimodaira, Kazuaki Matsuura, Yoji Kurosawa, Seiji Yoshida
  • Patent number: 8312725
    Abstract: A trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream, where the fuel includes hydrogen gas. The trapped vortex combustor is configured to receive the lean premixed fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion, and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.
    Type: Grant
    Filed: September 30, 2009
    Date of Patent: November 20, 2012
    Assignee: Ramgen Power Systems, LLC
    Inventors: Robert C. Steele, Ryan G. Edmonds, Joseph T. Williams, Stephen P. Baldwin
  • Publication number: 20120023952
    Abstract: A nozzle for assemblies and gas turbines is provided. The nozzle exhibits destabilized flame holding characteristics, i.e., the nozzle is unable to stabilize flame up to an equivalence ratio of about 0.65. As a result, flame heat release is delayed resulting in lower peak flame temperatures and correspondingly lower NOx levels. Flame stabilization capability is retained for higher equivalence ratios to support operation of the combustor in other regions of the load range.
    Type: Application
    Filed: July 30, 2010
    Publication date: February 2, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Christian Lee Vandervort, Joel Meier Haynes
  • Patent number: 8061144
    Abstract: In a by-pass gas turbine engine having a lobed type by-pass air and turbine exhaust mixer unit, the reheat gutters are arranged in the mixer in the turbine exhaust duct. The gutters extend radially and are substantially Y-shaped, each of the two legs of the Y extending radially along the sides of a mixer lobe.
    Type: Grant
    Filed: March 2, 1978
    Date of Patent: November 22, 2011
    Assignee: Rolls-Royce Limited
    Inventor: Addison Charles Maguire
  • Patent number: 8061143
    Abstract: A gas turbine reheat system is provided with channel-shaped gutters, with a wall portion spaced from each gutter to form a space therebetween. The space is supplied with cooling air conveniently from the engine by-pass duct.
    Type: Grant
    Filed: March 2, 1978
    Date of Patent: November 22, 2011
    Assignee: Rolls-Royce Limited
    Inventor: Addison Charles Maguire
  • Publication number: 20110219776
    Abstract: A flame stabilizer is in fluid communication with a combustor of a gas turbine engine. The flame stabilizer has a body with an aerodynamic shape that creates a flow recirculation zone by injection of fluid through a plurality of holes in the body of the flame stabilizer. The aerodynamic shape of the body reduces pressure loss in the combustor, particularly when no fuel is being provided to the combustor. In addition, the magnitude of the flow recirculation zone can be modulated by selectively adjusting the flow rate of fluid through the holes, or by selectively adjusting the size of the holes.
    Type: Application
    Filed: March 15, 2010
    Publication date: September 15, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Ronald Scott Bunker, Andrei Tristan Evulet
  • Patent number: 8001786
    Abstract: A combustor of gas turbine engine, including: a fuel spray portion that sprays fuel to create a diffusion combustion region in a combustion chamber, the fuel spray portion including a fuel atomizing portion that atomizes the fuel, and a diffusion passage portion disposed downstream of the fuel atomizing portion, the diffusion passage portion having a spreading trumpet-like shape and diffuses the fuel and the air; a pre-mixture supply portion that supplies a pre-mixture gas including the fuel and air to create a pre-mixture combustion region in the combustion chamber, the pre-mixture supply portion being positioned concentrically with the fuel spray portion to surround the fuel spray portion; and a fuel diffusion restraining member disposed on an inner circumferential face of the diffusion passage portion for restraining a diffusion of injected fuel by separating a stream of the injected fuel away from the inner circumferential face.
    Type: Grant
    Filed: February 11, 2008
    Date of Patent: August 23, 2011
    Assignee: Kawasaki Jukogyo Kabushiki Kaisha
    Inventors: Takeo Oda, Atsushi Horikawa, Hideki Ogata
  • Patent number: 7856828
    Abstract: A flameholder arm for an afterburner of a turbomachine, particularly a jet engine, is disclosed. The arm includes a ventilation duct which is centered and immobilized inside the arm independent of the heatshield. The duct also includes a transverse lip which includes an orifice for centering and guiding a fuel injection harness. The transverse lip prevents the harness from being positioned in any way incorrectly in the arm.
    Type: Grant
    Filed: March 29, 2007
    Date of Patent: December 28, 2010
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Nicolas Pierre-Marie Girard
  • Publication number: 20100269509
    Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.
    Type: Application
    Filed: January 23, 2007
    Publication date: October 28, 2010
    Inventors: Arthur J. Harris, JR., Rajeev Ohri
  • Publication number: 20100192583
    Abstract: A method for stabilizing the flame of a premixing burner, comprising a reaction chamber containing a fluid is provided. The method includes injecting an air-fuel mixture into the reaction chamber at a speed that is different from that of the fluid present in the reaction chamber, adjusting the speed such that vortices form at the boundary between the air-fuel mixture and the surrounding fluid. A premixing burner including a reaction chamber and at least one premixing spray nozzle opening into the reaction chamber is also provided. The premixing burner injects an air-fuel mixture into the reaction chamber at a speed that is different from that of the surrounding fluid, the speed being adjusted such that vortices from at the boundary between the air-fuel mixture and the surrounding fluid.
    Type: Application
    Filed: June 19, 2008
    Publication date: August 5, 2010
    Inventors: Mariano Cano Wolff, Patrick Ronald Flohr, Matthias Hase, Martin Lenze, Jürgen Meisl, Paul Pixner, Uwe Remlinger, Kai-Uwe Schildmache, Thomas Alexis Schneider, Jaap van Kampen
  • Patent number: 7658609
    Abstract: An internal combustion burner, especially for attenuation of mineral fibers, and including a combustion chamber, into which at least one duct for feeding fuel and oxidizer opens, and provided with an expansion orifice. The combustion chamber is provided with at least one flame stabilizing element, the geometry of the walls of which is chosen to create a confinement zone in which at least part of the combustion between oxidizer and fuel takes place.
    Type: Grant
    Filed: February 13, 2003
    Date of Patent: February 9, 2010
    Assignee: Saint-Gobain Isover
    Inventors: Oleg Boulanov, Christopher Ellison, Jean-Luc Bernard
  • Patent number: 7621132
    Abstract: The subject application is directed to burners for gas turbine engines that use a pilot flame to assist in sustaining and stabilizing the combustion process. An embodiment of the disclosed burners includes, inter alia, a burner housing, a pilot combustor and a quencher. The burner housing has axially opposed upstream and downstream end portions. Additionally, the housing has at least one main fuel inlet passage and at least one main air inlet passage which are adapted to supply fuel and air respectively to an internal chamber defined in the housing. The pilot combustor is disposed along the axis of the burner housing and has an inlet for receiving a rich fuel and air mixture, a combustion chamber within which the rich fuel and air mixture is combusted into combustion products, and an outlet for exhausting the combustion products from the combustion chamber. The quencher is disposed within the internal chamber of the burner housing along the central axis and positioned at the outlet of the pilot combustor.
    Type: Grant
    Filed: September 3, 2004
    Date of Patent: November 24, 2009
    Assignees: Delavan Inc., Siemens Aktiengesellschaft
    Inventors: Michael Cornwell, Vladimir Dusan Milosavljevic
  • Publication number: 20090282831
    Abstract: A modification method for reducing emissions from an annular shaped combustor of a gas turbine plant, having uniformly spaced circumferentially mounted premix burners (20), includes the steps of: removing at least one burner (20), thereby disrupting the spatial uniformity of the remaining the burners (20); and modifying the combustor air distribution system so as to compensate for the increased burner pressure drop of the remaining burners, thus enabling the modified combustor to operate at a load equivalent to the unmodified combustor. Emission reduction is enabled by the increase in the gas velocity of the burner for a given load further enabled by the flame stabilizing effect of disrupting the spatial uniformity.
    Type: Application
    Filed: May 7, 2009
    Publication date: November 19, 2009
    Inventors: Adnan Eroglu, Oliver Riccius, Klaus Knapp, Peter Flohr
  • Patent number: 7603841
    Abstract: A trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream, where the fuel includes hydrogen gas. The trapped vortex combustor is configured to receive the lean premixed fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion, and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.
    Type: Grant
    Filed: February 28, 2006
    Date of Patent: October 20, 2009
    Assignee: Ramgen Power Systems, LLC
    Inventors: Robert C. Steele, Ryan G. Edmonds, Joseph T. Williams, Stephen P. Baldwin
  • Publication number: 20090211255
    Abstract: A gas turbine combustor is presented, which includes a combustion chamber that is positioned downstream of a premixing chamber. The premixing chamber includes at least one opening for ingesting air. At least one primary fuel nozzle is disposed to discharge fuel into the premixing chamber. The fuel discharged from the primary fuel nozzle mixes with the ingested air in the premixing chamber to provide a fuel air mix. A secondary fuel nozzle is disposed proximate the combustion chamber to discharge fuel at the combustion chamber. A stabilizer is disposed at the secondary fuel nozzle so as to be positioned in close proximity to a flame when fuel at the secondary fuel nozzle is ignited. The stabilizer is composed of a material having the ability to absorb heat from a heat flux generated within the combustor and maintaining a temperature sufficient to sustain ignition of the flame. A method of stabilizing a flame in a gas turbine combustor is also presented.
    Type: Application
    Filed: February 21, 2008
    Publication date: August 27, 2009
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Derrick Walter Simons, Geoffrey D. Myers, Larry L. Thomas, Jeffrey Lebegue
  • Publication number: 20090204306
    Abstract: A method of combustion stability control for a gas turbine engine is provided, and includes the steps of receiving by a stability controller, information regarding environmental and operating conditions, and comparing the environmental and operating conditions to pre-programmed information to determine if a likelihood of combustion instability exists. The method further includes the steps of determining optimal fuel modulation frequency and amplitude for the environmental condition to reduce combustion instability, if a likelihood of combustion instability exists, and actuating at least one fuel modulation valve to, at the optimal fuel modulation frequency and amplitude, reduce combustion instability, if a likelihood of combustion instability exists. Systems for modulating fuel flow are also provided.
    Type: Application
    Filed: February 10, 2009
    Publication date: August 13, 2009
    Applicant: DELAVAN INC
    Inventors: Jerry Lee Goeke, Brandon Philip Williams
  • Publication number: 20090178414
    Abstract: A flame holder for an augmentor includes geometry to produce large radial variations in heat release to prevent coupling with modes within the exhaust duct that produce combustor screech. A surface of the flame holder varies axially in a radial direction to produce a radial phase variation in heat released from the flame holder. The radially changing surface produces radially non-uniform and unsteady heat release that does not couple with acoustic modes within the exhaust duct.
    Type: Application
    Filed: January 14, 2008
    Publication date: July 16, 2009
    Applicant: United Technologies Corporation
    Inventor: Oliver V. Atassi
  • Publication number: 20090113895
    Abstract: A trapped vortex combustor. The trapped vortex combustor is configured for receiving a lean premixed gaseous fuel and oxidant stream, where the fuel includes hydrogen gas. The trapped vortex combustor is configured to receive the lean premixed fuel and oxidant stream at a velocity which significantly exceeds combustion flame speed in a selected lean premixed fuel and oxidant mixture. The combustor is configured to operate at relatively high bulk fluid velocities while maintaining stable combustion, and low NOx emissions. The combustor is useful in gas turbines in a process of burning synfuels, as it offers the opportunity to avoid use of diluent gas to reduce combustion temperatures. The combustor also offers the possibility of avoiding the use of selected catalytic reaction units for removal of oxides of nitrogen from combustion gases exiting a gas turbine.
    Type: Application
    Filed: February 28, 2006
    Publication date: May 7, 2009
    Inventors: Robert C. Steele, Ryan G. Edmonds, Joseph T. Williams, Stephen P. Baldwin
  • Patent number: 7185494
    Abstract: A single stage combustor for a gas turbine having an annular array of outer fuel nozzles arranged about a center axis of the combustor; a center fuel nozzle aligned with the center axis, wherein the center fuel nozzle is substantially smaller than each of the outer fuel nozzles, wherein the combustor includes a pre-mix operating mode in which the center nozzle receives a fuel rich air-fuel mixture.
    Type: Grant
    Filed: April 12, 2004
    Date of Patent: March 6, 2007
    Assignee: General Electric Company
    Inventors: Willy Steve Ziminsky, Derrick W. Simons, Arthur James Fossum
  • Patent number: 7143583
    Abstract: A gas turbine combustor comprises a premixed combustion burner disposed on the periphery of a pilot burner, an approximately cylindrical combustor liner disposed on the downstream side of the premixed combustion burner, which defines a combustion chamber in the liner. The gas turbine combustor is characterized by further comprising flame stabilizers radially disposed at the exit of the premixed combustion burner, and a fuel injection means with which the pilot burner is provided injects at least one of gas fuel and liquid fuel, in which a plurality of air nozzles are provided which are located outside the pilot burner and inside the premixed combustion burner, and which spout out air into the combustion chamber. Adequate combustion can be accomplished with a combustor which is capable of using gas fuel and liquid fuel, and at the same time, NOx can be reduced.
    Type: Grant
    Filed: March 7, 2003
    Date of Patent: December 5, 2006
    Assignee: Hitachi, Ltd.
    Inventors: Akinori Hayashi, Shinichi Inage, Hiromi Koizumi, Isao Takehara, Kazuyuki Ito, Toshifumi Sasao, Hidetaro Murata
  • Patent number: 7062917
    Abstract: A combustion chamber (5) for a gas turbine is adapted for flameless oxidation of fuels. This circulation flow has an internal space (9) in which a large-volume circulation flow is established. To this end, the combustion chamber supplies a hot exhaust stream to the introduced air, the mass flow rate of which exceeds the fresh air stream. The fresh air and the fuel are fed to the combustion chamber in the same direction, roughly parallel to the wall.
    Type: Grant
    Filed: April 22, 2003
    Date of Patent: June 20, 2006
    Assignee: WS Warmeprozesstechnik GmbH
    Inventors: Joachim G. Wunning, Joachim A. Wunning
  • Patent number: 7003961
    Abstract: A trapped vortex combustor for gas turbine engines. An annular combustor housing is provided having a plurality of inlet centerbodies disposed along a helical axis. The inlet centerbodies include a leading edge structure, opposing sidewalls, a pressurizable cavity, and a rear wall. Inlet centerbodies cooperate with adjacent structure and an aft bluff body to define a trapped vortex cavity combustion chamber for mixing an inlet fluid and burning fuel to form hot combustion gases. Mixing is enhanced by utilizing struts adjacent to the rear wall to create eddies in the fluid flow, and by injecting fuel and/or air in opposition to swirl created by the bulk fluid flow. Hot combustion gases are utilized in a turbine for extraction of kinetic energy, or in heat exchange equipment for recovery of thermal energy. High combustion efficiencies and less than 10 ppm emissions of oxides of nitrogen and of carbon monoxide are achieved.
    Type: Grant
    Filed: May 5, 2003
    Date of Patent: February 28, 2006
    Assignee: Ramgen Power Systems, Inc.
    Inventors: Donald Kendrick, Shawn P. Lawlor, Robert C. Steele
  • Patent number: 6996990
    Abstract: A flow controller is disposed between a preburner section in a diffuser and prior to the main fuel injector and catalytic sections in a turbine combustor. The flow from the burner section is typically not uniform in temperature and velocity and the flow splitter renders the flow substantially uniform at the fuel injector and catalyst inlet. The flow splitter comprises substantially equal mass annular flow areas defined by a first outer frustoconical element and the diffuser wall, a second element defining with the first element a second annular area and a central bluff disk defining with the second element the interior annular area. Vanes are provided on the flow splitter to enhance turbulent flow and substantially preclude swirling flow. As a result, flow uniformity at the catalyst inlet and main fuel injection is achieved.
    Type: Grant
    Filed: August 27, 2003
    Date of Patent: February 14, 2006
    Assignee: General Electric Company
    Inventor: Constantin Alexandru Dinu
  • Patent number: 6971239
    Abstract: A gas turbine engine augmentor nozzle has an inlet for connection to an augmentor fuel conduit and an outlet for expelling a spray of fuel. A passageway between the inlet and outlet is at least partially bounded by outlet end surface portions diverging from each other. The nozzle may be used as a replacement for a non-divergent nozzle and may reorient a fuel jet centerline toward radial.
    Type: Grant
    Filed: May 13, 2003
    Date of Patent: December 6, 2005
    Assignee: United Technologies Corporation
    Inventors: Timothy S. Snyder, Christopher R. Brdar, John R. Buey
  • Patent number: 6968694
    Abstract: A turbine engine has a centerbody within a gas flowpath and a downstream tailcone and a pilot at an upstream end of the tailcone. A flameholder is positioned in the flowpath outboard of the centerbody. The pilot has a first surface diverging in a downstream direction.
    Type: Grant
    Filed: March 13, 2003
    Date of Patent: November 29, 2005
    Assignee: United Technologies Corporation
    Inventors: John R. Buey, John M. Bonnell
  • Patent number: 6923001
    Abstract: A pilotless catalytic combustor (10) including a basket (12) having a central axis (14) and a central core region (16) disposed along a portion of the central axis. Catalytic combustion modules (18) are circumferentially disposed about the central axis radially outward of the central core region for receiving a fuel flow (20) and a first portion of an oxidizer flow (22), and discharge a partially oxidized fuel/oxidizer mixture (24) at respective exit ends (26). A base plate (30) is positioned in the central core region upstream of the exit ends of the catalytic combustion modules, the baseplate defining a recirculation zone (32) near the respective exit ends for stabilizing oxidation in the burnout zone. A method of staged fueling for a pilotless catalytic combustor includes providing fuel to at least one of the modules during start up and progressively providing fuel to other modules as a load on the turbine engine is increased.
    Type: Grant
    Filed: July 14, 2003
    Date of Patent: August 2, 2005
    Assignee: Siemens Westinghouse Power Corporation
    Inventors: Walter Ray Laster, Ramarao V. Bandaru
  • Patent number: 6895756
    Abstract: An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and a central recirculation zone, which is positioned within the outer recirculation zone. These recirculation zones are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers. The recirculation zones accelerate flame propagation to allow afterburning to be completed in a relatively short length.
    Type: Grant
    Filed: February 6, 2003
    Date of Patent: May 24, 2005
    Assignee: The Boeing Company
    Inventors: Stephen N. Schmotolocha, Donald H. Morris, Robert J. Pederson, Raymond B. Edelman, Calvin Q. Morrison, Jr.
  • Patent number: 6845621
    Abstract: An annular combustor has an annular inner shell, an annular outer shell and a dome end wall connecting the inner shell with the outer shell. A dam is positioned between the dome end wall and the exit end and extends radially from at least one of the inner shell and the outer shell to provide a reduced flow area passageway within the combustion chamber.
    Type: Grant
    Filed: May 1, 2001
    Date of Patent: January 25, 2005
    Assignee: Elliott Energy Systems, Inc.
    Inventor: J. Michael Teets
  • Patent number: 6668557
    Abstract: A pilot nozzle of a gas turbine combustor comprises a first structure, provided near a main nozzle of a combustor that injects fuel oil, having a flow channel for a fuel gas and an outlet for the fuel gas. The first structure diffusion-injecting the fuel gas obliquely forward through the outlet to maintain a flame and to aid ignition of the fuel oil injected from the main nozzle. There is further provided a second structure which circulates in whirls a combustion gas generated due to the combustion of the fuel gas.
    Type: Grant
    Filed: July 23, 2002
    Date of Patent: December 30, 2003
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Masataka Ohta, Kuniaki Aoyama, Mitsuru Inada, Shigemi Mandai, Satoshi Tanimura, Katsunori Tanaka, Koichi Nishida
  • Patent number: 6575733
    Abstract: The invention relates to a method for combustion of fuels of arbitrary state of aggregation, which are burnt with air, possibly with the addition of water, and a reactor therefore, which is intended to optimize the combustion method. A solid, liquid and/or gaseous fuel, possibly water and/or an oxidizing agent are introduced into a reaction chamber (2) in its axial direction under high pressure, the amount of injected pressurized air corresponding to the amount of air necessary for the complete combustion, and the introduced mixture is led to a deflection surface (7) in the interior of the reaction chamber (2), whereby it is atomized, sublimates and/or evaporates and burns explosively, before it can reach the wall or the bottom of the reaction chamber (2).
    Type: Grant
    Filed: August 17, 2000
    Date of Patent: June 10, 2003
    Assignee: Gourmeli International N.V.
    Inventor: Franz Josef Staffer