| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060738000 | Premix tube within combustion zone | 31 |
| 20080229752 | FUEL LANCE | 09-25-2008 |
| 20080276618 | METHOD AND SYSTEM FOR POROUS FLAME HOLDER FOR HYDROGEN AND SYNGAS COMBUSTION - A mixing region of a fuel nozzle assembly for a combustor in a gas turbine, the assembly including: a gaseous fuel nozzle having a center axis and extending along the center axis, the fuel nozzle including a gaseous fuel passage and a fuel nozzle at a distal end of the passage; an air tube concentric with the fuel nozzle and defining an air passage between the air tube and the fuel nozzle, wherein the air tube includes a distal section extending axially beyond the fuel injection nozzle; a first fuel-air mixing zone defined by and inside the distal section of the air tube, wherein said first fuel-air mixing zone is downstream of the fuel injection nozzle; a flame holder comprising a porous structure with thermal barrier coating and micro swirlers and defining a downstream end of the first fuel-air mixing zone, wherein fuel and air from the first fuel-air mixing zone pass through the porous structure of the flame holder and into a combustion zone of the combustor. | 11-13-2008 |
| 20090019854 | APPARATUS/METHOD FOR COOLING COMBUSTION CHAMBER/VENTURI IN A LOW NOx COMBUSTOR - A dry low nitric oxides (NOx) emissions combustor includes a premixing chamber for mixing fuel and cooling gas and a combustion chamber positioned downstream of the premixing chamber for the combustion of pre-mixed fuel and cooling gas. The combustor further includes a venturi having generally annular walls including converging and diverging wall portions that define a constricted portion and positioned between the premixing chamber and the combustion chamber through which the premixed fuel and air pass to the combustion chamber. The walls defining a passage for cooling gas flow extending axially along the combustion chamber and having an exit for flowing cooling gas to the combustion chamber. A plurality of inlets at the converging and diverging wall portions ingest cooling gas into the passage to produce an impingement cooling effect. A plurality of tubulators disposed downstream of the inlets interact with the cooling gas to produce a turbulated cooling effect. The combustor may be effectively fired over a substantial temperature range to reduce the NOx emissions of the combustor. | 01-22-2009 |
| 20090019855 | Low emissions gas turbine combustor - A gas turbine combustor including: a primary combustion chamber; a secondary combustion chamber downstream of the primary combustion chamber; a venturi having a venturi throat; a transition piece; a cap assembly attached to the primary combustion chamber, and an external turbulator member in operable communication with the cap assembly, wherein the primary combustion chamber includes a mixing hole arrangement for improving homogeneity of an air and fuel mixture in the combustor; the venturi throat is disposed within a predetermined distance upstream from the downstream end of the primary combustion chamber; the transition piece is composed of a duct body, with a plurality of dilution holes formed in the duct body; and the external turbulator member includes a step positioned at the second end of the centerbody, the step defining a radial distance about the second end of the centerbody. | 01-22-2009 |
| 20090107147 | Gas turbine fuel injector with removable pilot liquid tube - A fuel injector for a gas turbine engine is disclosed. The fuel injector includes an injector housing having a longitudinal axis. The injector housing includes one or more fuel galleries annularly disposed about the longitudinal axis, and a compressed air inlet. The fuel injector also includes a premix barrel having a proximal end and a distal end circumferentially disposed about the longitudinal axis. The premix barrel is fluidly coupled to the fuel galleries and the compressed air inlet at the proximal end and is configured to couple to a combustor of the gas turbine engine at the distal end. The fuel injector also includes a substantially cylindrical pilot assembly disposed radially inwards of the premix barrel having a first end and a second end. The second end is coupled to the injector housing and the first end is located proximate the distal end of the premix barrel. The fuel injector further includes a pilot liquid tube having a third end and a fourth end disposed radially inwards of the pilot assembly. The fourth end is removably coupled to the injector housing and the third end is located proximate the first end of the pilot assembly. | 04-30-2009 |
| 20100186412 | ANNULAR FUEL AND AIR CO-FLOW PREMIXER - Disclosed is a premixer for a combustor including an annular outer shell and an annular inner shell. The inner shell defines an inner flow channel inside of the inner shell and is located to define an outer flow channel between the outer shell and the inner shell. A fuel discharge annulus is located between the outer flow channel and the inner flow channel and is configured to inject a fuel flow into a mixing area in a direction substantially parallel to an outer airflow through the outer flow channel and an inner flow through the inner flow channel. Further disclosed are a combustor including a plurality of premixers and a method of premixing air and fuel in a combustor. | 07-29-2010 |
| 20100212322 | COAXIAL FUEL AND AIR PREMIXER FOR A GAS TURBINE COMBUSTOR - An air/fuel premixer comprising a peripheral wall defining a mixing chamber, a nozzle disposed at least partially within the peripheral wall comprising an outer annular wall spaced from the peripheral wall so as to define an outer air passage between the peripheral wall and the outer annular wall, an inner annular wall disposed at least partially within and spaced from the outer annular wall, so as to define an inner air passage, and at least one fuel gas annulus between the outer annular wall and the inner annular wall, the at least one fuel gas annulus defining at least one fuel gas passage, at least one air inlet for introducing air through the inner air passage and the outer air passage to the mixing chamber, and at least one fuel inlet for injecting fuel through the fuel gas passage to the mixing chamber to form an air/fuel mixture. | 08-26-2010 |
| 20110005230 | FUEL NOZZLE ASSEMBLY FOR A GAS TURBINE ENGINE - A fuel nozzle assembly for a gas turbine engine includes a flange and a pre-mix tube. The flange includes a first end that is configured to couple to an end cover of the combustor, and a second end that is opposite said first end. The pre-mix tube is coupled at a first end to the flange second end. The flange and the pre-mix tube are fabricated to operate at a natural frequency that is different from an operating frequency of the gas turbine engine. | 01-13-2011 |
| 20110179797 | Burner and method for operating a burner - A burner and a method for operating a burner are provided. The burner includes a channel having a mixing zone and having a feed for an oxidation means, particularly an air feed, and at least one fuel feed for injecting fuel, wherein a separating means which divides the channel over a wide range of the channel into at least two separated channels, namely a first channel and a second channel, is provided in the channel. The method for operating a burner having a channel includes a mixing zone into which an oxidation mass flow and fuel are injected, wherein two substantially separate flow paths are formed by means of a separating means in the channel and the at least two separated first and second channels, formed by the separating means. | 07-28-2011 |
| 20120031097 | MULTI-PREMIXER FUEL NOZZLE - The present application provides a fuel nozzle for use in a gas turbine. The fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers. | 02-09-2012 |
| 20120036856 | DIMPLED/GROOVED FACE ON A FUEL INJECTION NOZZLE BODY FOR FLAME STABILIZATION AND RELATED METHOD - A fuel injection head for a fuel nozzle used in a gas turbine combustor includes a substantially hollow body formed with an upstream end face, a downstream end face and a peripheral wall extending therebetween. A plurality of pre-mix tubes or passages extend axially through the hollow body with inlets at the upstream end face and outlets at the downstream end face. An exterior surface of the downstream end face is formed with three-dimensional surface features that increase a total surface area of the exterior surface as compared to a substantially flat, planar downstream end face. | 02-16-2012 |
| 20120144833 | Arrangement for Preparation of a Fuel for Combustion - 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. | 06-14-2012 |
| 20120198850 | GAS TURBINE ENGINE AND FUEL INJECTION SYSTEM - One embodiment of the present invention is a unique gas turbine engine. Another embodiment is a unique fuel injection system for a gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and fuel injection systems for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith. | 08-09-2012 |
| 20130067920 | FUEL INJECTOR AND SWIRLER ASSEMBLY WITH LOBED MIXER - Disclosed is a gas turbine fuel injector and swirler assembly, including: a delivery tube structure arranged on a central axis of the fuel injector and swirler assembly, a first fuel supply channel arranged in the delivery tube structure, a shroud surrounding the delivery tube structure, swirl vanes arranged between the delivery tube structure and the shroud, a radial passage in each swirl vane, communicating with the first fuel supply channel, a set of apertures open between the radial passage and the exterior surface of said each swirl vane, wherein a second fuel supply channel is arranged in the delivery tube structure extending to a downstream end of the delivery tube structure and a mixer with lobes for fuel injection is arranged at the downstream end. Further disclosed is an assembly method for assembling a fuel injector and swirler assembly. | 03-21-2013 |
| 20130104552 | FUEL NOZZLE ASSEMBLY FOR USE IN TURBINE ENGINES AND METHODS OF ASSEMBLING SAME | 05-02-2013 |
| 20130167541 | Air-Fuel Premixer for Gas Turbine Combustor with Variable Swirler - A swirler assembly in a gas turbine combustor includes a hub, a shroud, and a plurality of vanes connected between the hub and the shroud. A vane angle of the plurality of vanes is adjustable. | 07-04-2013 |
| 20130167542 | FLOWSLEEVE OF A TURBOMACHINE COMPONENT - A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture. | 07-04-2013 |
| 20130219899 | ANNULAR PREMIXED PILOT IN FUEL NOZZLE - A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits that are configured with concentric axes that direct the fuel/air mixture axially from the premixed pilot nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix and including air jets that direct air radially outwardly from the premix conduits. | 08-29-2013 |
| 20140013763 | FUEL-AIR PRE-MIXER WITH PREFILMER - A fuel-air premixer for a combustor of a gas turbine engine includes a central passage disposed along an axis and operable to communicate a first airflow and an outer annular passage about the axis operable to communicate a second airflow. The fuel-air premixer further includes an inner annular passage about the axis and between the central passage and the outer annular passage for communicating fuel flow. The inner annular passage including an inner exit angled for directing fuel flow toward the axis into a mixer passage downstream of the outer and inner exits for mixing the fuel flow with the first and second airflows. | 01-16-2014 |
| 20140144144 | Gas Turbine Combustor - A gas turbine combustor includes: multiple gaseous fuel nozzles to inject gaseous fuel; a manifold to distribute gaseous fuel to the multiple gaseous fuel nozzles; a burner flange to secure a burner to an end cover; and a burner body to connect the manifold and the burner flange. Gaseous fuel passages are provided in the end cover, the burner flange, and the burner body. The gaseous fuel passage communicates with the manifold. A second manifold is provided in the burner flange. The gaseous fuel passage is provided in the burner body to make the second manifold communicate with the first mentioned manifold. | 05-29-2014 |
| 20140190169 | Coaxial Fuel Supply for a Micromixer - Embodiments of the present application can provide systems and methods for a coaxial fuel supply for a micromixer. According to one embodiment, the micromixer may include an elongated base nozzle structure, a number of mixing tubes in communication with the elongated base nozzle structure, and an air inlet configured to supply the plurality of mixing tubes with air. The elongated base nozzle structure may be configured to supply a fuel to the mixing tubes. | 07-10-2014 |
| 20140338340 | SYSTEM AND METHOD FOR TUBE LEVEL AIR FLOW CONDITIONING - A system includes a multi-tube fuel nozzle. The multi-tube fuel nozzle includes multiple tubes. Each tube includes a first end, a second end, and an annular wall disposed about a central passage. The first end is configured to be disposed about a fuel injector. Each tube also includes an air flow conditioner having multiple air ports disposed adjacent the first end. The multiple air ports extend through the wall into the central passage. | 11-20-2014 |
| 20140366542 | Fuel Air Premix Chamber For a Gas Turbine Engine - Fuel/air premixing chambers are applied to a gas turbine combustor RQL or LPP type integrated to the combustor with extension into the combustion zone. An integral heat exchange structure cools the premix chamber outer wall, preheating the compressor air supply as it passes into an inner central longitudinal premix tube preheating also the fuel and F/A mixture for improved mixedness, low emissions combustion and low differential combustor pressure. | 12-18-2014 |
| 20150135718 | COMBUSTOR AND METHOD FOR DISTRIBUTING FUEL IN THE COMBUSTOR - A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface, and a plurality of tubes extend from the upstream surface through the downstream surface to provide fluid communication through the tube bundle. A barrier extends radially inside the tube bundle between the upstream and downstream surfaces, and a baffle extends axially inside the tube bundle between the upstream surface and the barrier. | 05-21-2015 |
| 20150362193 | COMBUSTOR AND GAS TURBINE - A combustor of the present invention includes: a pilot burner; a plurality of main burners ( | 12-17-2015 |
| 20160025346 | GAS TURBINE COMBUSTOR - A combustor is capable of ignition and flame propagation at low fuel concentrations for gas or liquid fuel. Combustors are disposed annularly along an outer peripheral portion of a casing of a turbine. A combustion chamber burns fuel and air to generate a combustion gas. A diffusion burner is disposed upstream of the combustion chamber; and a plurality of premix burners are disposed around the diffusion burner. Cross fire tubes provide communication between combustion chambers of combustors adjacent to each other. A cross fire tube connected to a combustor adjacent to a first side in the circumferential direction of the casing is disposed so as to have a central axis passing over a premix burner as viewed from the combustion chamber and another cross fire tube connected to the combustor adjacent to a second side is disposed so as to have a central axis passing between two premix burners. | 01-28-2016 |
| 20160040882 | FUEL NOZZLE TUBE RETENTION - A system for retaining a fuel nozzle premix tube includes a retention plate and a premix tube which extends downstream from an outlet of a premix passage defined along an aft side of a fuel plenum body. The premix tube includes an inlet end and a spring support feature which is disposed proximate to the inlet end. The premix tube extends through the retention plate. The spring retention feature is disposed between an aft side of the fuel plenum and the retention plate. The system further includes a spring which extends between the spring retention feature and the retention plate. | 02-11-2016 |
| 20160116169 | MIXER RETENTION - Aspects of the disclosure are directed to methods and systems associated with a gas turbine engine of an aircraft. In some embodiments, a surface of a liner of the gas turbine engine is coupled to a fuel/air mixer, and a surface of a panel of the engine is coupled to the mixer such that a portion of the mixer is disposed between the liner surface and the panel surface. | 04-28-2016 |
| 20160123595 | COMBUSTOR ARRANGEMENT FOR A GAS TURBINE - A combustor arrangement for a gas turbine includes a first burner, a first combustion chamber, a mixer for admixing a dilution gas to the gases leaving the first combustion chamber during operation, a second burner, and a second combustion chamber arranged sequentially in a fluid flow connection. These elements of the combustor arrangement are arranged in a row to form a flow path extending between the first combustion chamber and the second burner. The arrangement includes a central lance body in the flow path, extending from the first burner into the second burner, which lance body includes at least one air duct for providing air for the mixer, wherein the air is injected into the combustor through air supply elements. | 05-05-2016 |
| 20160178206 | FUEL INJECTOR | 06-23-2016 |
| 20160377293 | FUEL INJECTOR SYSTEMS - In accordance with at least one aspect of this disclosure, a fuel injector system can include an air mixer defining an outer air circuit, at least one intermediate air circuit, and an inner air circuit. The fuel injector system can also include a fuel manifold defining a fuel circuit, at least a portion of which is operatively disposed within the air mixer such that the fuel circuit and the intermediate air circuit are in fluid communication with each other for atomization of fuel. At least one of the air mixer or the fuel manifold can be additively manufactured. | 12-29-2016 |
