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| Number | Title | Issue Date |
| 8104284 | Combustor and a fuel supply method for the combustor A combustor includes a chamber mixing and burning fuel and air and an air hole plate disposed on a wall surface of the chamber. The, air hole plate includes a plurality of rows disposed concentrically of a plurality of air holes jetting coaxial jets of fuel and air ... | 01/31/2012 |
| 7905093 | Apparatus to facilitate decreasing combustor acoustics A method for operating a gas turbine engine including a compressor and a combustor is provided. The method comprises channeling between about 0% to about 8% of the total airflow discharged from a compressor towards a pilot swirler coupled within the burner, wherein ... | 03/15/2011 |
| 7827797 | Injection assembly for a combustor An injection assembly for use with a combustor is provided. The injection assembly includes an effusion plate that has a plurality of plate openings and a plate sleeve having a sidewall portion that includes a forward edge. The forward edge is coupled to the effusio... | 11/09/2010 |
| 7797942 | Gas turbine combustor having multiple independently operable burners and staging method thereof In a combustor of a gas turbine which has a pilot nozzle being installed to the center of the axis of a combustor basket and a plurality of main nozzles being installed to the vicinity of the pilot nozzle and provided with a premixing tool on the outer circumference... | 09/21/2010 |
| 7757491 | Fuel nozzle for a gas turbine engine and method for fabricating the same A method for fabricating a fuel nozzle assembly includes providing a nozzle portion including a fuel passageway defined about a center axis of the fuel nozzle assembly. A longitudinal axis of a first peg is oriented to intersect the fuel nozzle assembly center axis ... | 07/20/2010 |
| 7673456 | Turbomachine combustion chamber with helical air flow A turbomachine combustion chamber includes an inner annular wall, an outer annular wall surrounding the inner wall so as to co-operate therewith to define an annular space forming a combustion area, a plurality of fuel injector systems including pilot injectors alte... | 03/09/2010 |
| 7614234 | Turbomachine combustion chamber with helical air flow The invention relates to a turbomachine combustion chamber having an inner wall, an outer wall surrounding the inner wall so as to co-operate therewith to define a space forming a combustion area, a transverse wall interconnecting the inner and outer walls, and fuel... | 11/10/2009 |
| 7546735 | Low-cost dual-fuel combustor and related method A combustor for a gas turbine includes a combustion chamber and a plurality of radially outer nozzles surrounding a single, center nozzle, the radially outer nozzles configured to supply only gas fuel to the combustion chamber and the center nozzle configured to sup... | 06/16/2009 |
| 7506511 | Reduced exhaust emissions gas turbine engine combustor A gas turbine engine combustor includes a plurality of main fuel injector assemblies, and a plurality of pilot fuel injector assemblies, that are arranged and configured to reduce exhaust gas emissions during engine operation. The plurality of main fuel injector ass... | 03/24/2009 |
| 7441398 | NOx adjustment system for gas turbine combustors An embodiment may comprise a system for controlling NOx emissions from a turbine having combustion chambers. The system may comprise a center fuel flow and a plurality of outer fuel flows for each of a plurality of combustion chambers. An outer fuel flow is set to a... | 10/28/2008 |
| 7360364 | Method and apparatus for assembling gas turbine engine combustors A method enables a combustor for a gas turbine engine to be assembled. The method includes coupling an inner liner to an outer liner such that a combustion chamber is defined therebetween, wherein the outer liner is fabricated from a plurality of panels coupled toge... | 04/22/2008 |
| 7343745 | Gas turbine combustor and operating method thereof A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 03/18/2008 |
| 7313919 | Gas turbine combustor A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 01/01/2008 |
| 7302801 | Lean-staged pyrospin combustor A combustor assembly includes a combustor chamber having a primary and intermediate zone that provides for reduced flame temperatures. The combustor assembly includes first and second pluralities of injectors. The first plurality of injectors introduces fuel to a pr... | 12/04/2007 |
| 7299618 | Gas turbine combustion apparatus A gas turbine combustion apparatus has a plurality of combustors provided in a circumferential direction within a turbine casing chamber formed by a casing, each combustor comprising a combustor inner tube and a combustor transition pipe, but lacks a turbine bypass ... | 11/27/2007 |
| 7287382 | Gas turbine combustor end cover An end cover for a gas turbine combustor that eliminates the use of braze joints within the plate portion of the end cover is disclosed. The end cover comprises a plate and a plurality of fluid inlets with the fluid inlets directing fluids to first and second manifo... | 10/30/2007 |
| 7278256 | Pulsed combustion engine A pulsed combustion apparatus includes a conduit having an outer wall and an inner wall. The inner wall has a number of apertures. An interior space is separated from the outer wall by the inner wall. An induction system is positioned to cyclicly admit charges to th... | 10/09/2007 |
| 7269958 | Combustor exit duct A combustor for a gas turbine engine includes a sheet metal combustor wall having a plurality of cooling apertures therein immediately upstream of a corner between two intersecting combustor wall portions. ... | 09/18/2007 |
| 7249721 | Device and method for injecting a liquid fuel into an air flow for a combustion chamber The present invention relates to a device for injecting a liquid fuel into a pressurized air flow (7), in particular for a combustion chamber, comprising a hollow cylindrical body (10) of longitudinal axis (YY′) delimiting a substantially cylindrical... | 07/31/2007 |
| 7222488 | Fabricated cowl for double annular combustor of a gas turbine engine A fabricated cowl for a double annular combustor of a gas turbine engine having a longitudinal axis extending therethrough, including an outer annular portion, an inner annular portion, and a middle annular portion. A plurality of circumferentially spaced radial slo... | 05/29/2007 |
| 7219498 | Waffled impingement effusion method A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal s... | 05/22/2007 |
| 7216488 | Methods and apparatus for cooling turbine engine combustor ignition devices An ignition device assembly for a gas turbine engine combustor includes a body and a shroud. The body extends from an inlet end to an outlet end, and the shroud extends circumferentially around at least a portion of the body, and axially from a first end to a tip en... | 05/15/2007 |
| 7200998 | Gas turbine combustor and operating method thereof A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 04/10/2007 |
| 7188476 | Gas turbine combustor and operating method thereof A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 03/13/2007 |
| 7185497 | Rich quick mix combustion system A premix chamber for a combustor of a gas turbine engine comprises a cylindrical chamber having a premix chamber wall, the cylindrical chamber having a chamber inlet end longitudinally separated from a chamber outlet end along a central axis, a chamber inlet plate i... | 03/06/2007 |
| 7185494 | Reduced center burner in multi-burner combustor and method for operating the combustor 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 ... | 03/06/2007 |
| 7181914 | Diffuser for gas turbine engine A gas turbine engine pre-diffuser 40 is generally annular, including radially inner and radially outer walls 40 and 42 and a generally cylindrical midline 48 defined between the walls. The pre-diffuser 40 includes a central member ... | 02/27/2007 |
| 7171813 | Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine A fuel injection nozzle has a cylindrical nozzle body having a cavity where fuel passes through. A plurality of hollow spokes, each having an aerofoil cross section, are provided around the nozzle body. Each hollow spoke has four fuel injection holes in total on bot... | 02/06/2007 |
| 7162875 | Method and system for controlling fuel supply in a combustion turbine engine In order to regulate fuel flow to the combustor (36) of the combustion turbine engine (10) having a primary combustion zone (64) and at least one further combustion zone, the temperature of the inlet and outlet of the combustor (36) are d... | 01/16/2007 |
| 7159403 | Apparatus for assembling gas turbine engine combustors A method for assembling a gas turbine engine combustor facilitates reducing costs and time required for assembly. The combustor includes a spectacle plate, a plurality of swirlers, and a plurality of deflector plates. The method includes coupling an assembly fixture... | 01/09/2007 |
| 7155913 | Turbomachine annular combustion chamber The invention relates to a turbomachine annular combustion chamber (1) comprising an outer axial wall (2), an inner axial wall (4), and a chamber bottom end (8) connecting the said walls, the chamber bottom end being provided with several... | 01/02/2007 |
| 7143583 | Gas turbine combustor, combustion method of the gas turbine combustor, and method of remodeling a gas turbine combustor 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 line... | 12/05/2006 |
| 7137256 | Method of operating a combustion system for increased turndown capability A method of operating a gas turbine engine combustion system at lower load conditions while maintaining required emissions levels is disclosed. The present invention includes multiple embodiments of axial, radial, and circumferential fuel staging within a can-type c... | 11/21/2006 |
| 7121095 | Combustor dome assembly of a gas turbine engine having improved deflector plates A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface, and a plurality of circumferentially spaced openings forme... | 10/17/2006 |
| 7117679 | Fuel injection In order to allow dual fuel operation, that is to say gas and liquid fuel, a fuel injection arrangement and an assembly are provided in which an injection conduit provides constriction to an airflow towards an outlet. In an assembly a plurality of arrangements inclu... | 10/10/2006 |
| 7117676 | Apparatus for mixing fluids A premixer for a combustor to entrain a selected volume of fuel in an oxidizer to be combusted to heat the oxidizer. The combustor is for a gas powered turbine which employs the hypergolic or high energy air stream which will allow a fuel to be combusted in the abse... | 10/10/2006 |
| 7117677 | Gas turbine combustor and operating method thereof A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets. ... | 10/10/2006 |
| 7107772 | Multi-point staging strategy for low emission and stable combustion The present invention relates to an improved multi-point injector for use in a gas turbine engine or other types of combustors. The multi-point fuel injector has a plurality of nozzles arranged in at least two arrays such as concentric rings. The injector further ha... | 09/19/2006 |
| 7107773 | Turbine engine sequenced combustion Aspects of the invention relate to a method for facilitating the reduction of carbon monoxide emissions during part load operation of a turbine engine by holding high combustor temperatures. The combustor section of the turbine engine includes a plurality of combust... | 09/19/2006 |
| 7096671 | Catalytic combustion system and method Aspects according to the invention relate to a catalytic combustor system for a turbine engine and an associated method. Catalytic combustors are used in connection with turbine engines because they can minimize the formation of oxides of nitrogen during combustion.... | 08/29/2006 |
