Class / Patent application number | Description | Number of patent applications / Date published |
060732000 | Having initial fuel-rich combustion zone | 15 |
20120304647 | REVERSE-FLOW ANNULAR COMBUSTOR FOR REDUCED EMISSIONS - A combustor for a gas turbine engine is provided. The combustor includes an inner liner; an outer liner circumscribing the inner liner; and a combustor dome having a first edge coupled to the inner liner and a second edge coupled to the outer liner. The combustor dome forms a combustion chamber with the inner liner and the outer liner. The combustion chamber receives air flow through the inner and outer liners, and the combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the inner liner and a second stream directed to the outer liner. | 12-06-2012 |
20140109581 | REVERSE-FLOW ANNULAR COMBUSTOR FOR REDUCED EMISSIONS - A combustor for a gas turbine engine is provided. The combustor includes an annular inner liner; an annular outer liner circumscribing the annular inner liner; and a combustor dome having a first edge coupled to the annular inner liner and a second edge coupled to the annular outer liner, the combustor dome forming a combustion chamber with the annular inner liner and the annular outer liner. The combustion chamber accommodates fluid flow through the annular inner and annular outer liners. The combustion chamber converges in the direction of the air flow to reduce a diameter of the combustion chamber. The combustor dome is configured to bifurcate the air flow at the combustor dome into a first stream directed to the annular inner liner and a second stream directed to the annular outer liner. | 04-24-2014 |
060733000 | Separate fuel injectors for plural zones | 13 |
20080256954 | START FLOW MEASUREMENT - A method and apparatus for measuring a start fuel flow to a pilot nozzle of a fuel system of a gas turbine engine using pressure differential between fuel passages leading to fuel nozzles. | 10-23-2008 |
20090049837 | GAS TURBINE ENGINE AIR VALVE ASSEMBLY - A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air through the first and second elements. An actuator is coupled by a linkage to the second element. A plurality of follower member assemblies each have an insertion portion extending through a corresponding first aperture in the first valving element and a corresponding second aperture in the second element. The insertion portion is circumferentially fixed relative to one of the first and second valving elements and circumferentially moveable relative to the other of the first and second valving elements. | 02-26-2009 |
20130008168 | BURNER FOR STABILIZING THE COMBUSTION OF A GAS TURBINE - A burner for stabilizing the combustion of a gas turbine is provided. The burner includes a combustion chamber and a plurality of nozzles opening out into the combustion chamber wherein fluid is introduced into the combustion chamber by the nozzles in the form of a fluid jet, wherein the fluid is burned in the combustion chamber to fatal a hot gas, wherein an annular gap is provided in the case of at least one nozzle for feeding the fluid to the nozzle at a nozzle inlet, wherein a preheater is provided for heating the fluid before entering the nozzle, wherein the preheater is a pre-burner with or without a combustion chamber, and wherein the pre-burner with or without a combustion chamber is arranged in the annular gap. | 01-10-2013 |
20130283800 | SYSTEM FOR SUPPLYING FUEL TO A COMBUSTOR - A system for supplying fuel to a combustor includes a combustion chamber, a liner that circumferentially surrounds at least a portion of the combustion chamber, and a flow sleeve that circumferentially surrounds at least a portion of the liner. A tube provides fluid communication for a working fluid to flow through the flow sleeve and the liner and into the combustion chamber, and the tube includes a tube wall. A plurality of fuel ports through the tube wall provide fluid communication for fuel to flow through the tube wall and into the tube, and the fuel ports are non-circular. | 10-31-2013 |
20130283801 | SYSTEM FOR SUPPLYING FUEL TO A COMBUSTOR - A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum. | 10-31-2013 |
20130298560 | SYSTEM FOR SUPPLYING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber downstream from the fuel nozzle, and a flow sleeve that circumferentially surrounds the combustion chamber. A plurality of fuel injectors are circumferentially arranged around the flow sleeve to provide fluid communication through the flow sleeve to the combustion chamber. A distribution manifold circumferentially surrounds the plurality of fuel injectors, and a fluid passage through the flow sleeve and into the distribution manifold provides fluid communication through the flow sleeve to the plurality of fuel injectors. | 11-14-2013 |
20140238024 | RICH BURN, QUICK MIX, LEAN BURN COMBUSTOR - A combustor for a gas turbine includes a fuel nozzle having a central swirler that circumferentially surrounds a downstream end of the fuel nozzle. A primary combustion zone is defined within the central swirler. The combustor further includes an outer swirler that circumferentially surrounds at least a portion of the central swirler and a venturi that is disposed downstream from the primary combustion zone. The venturi includes an inner surface. The central swirler imparts angular swirl to a compressed working fluid so as to rapidly mix and react the fuel rich primary zone products with the working fluid. The outer swirler imparts angular swirl to a compressed working fluid so as to provide a cooling boundary layer along the inner surface of the venturi. | 08-28-2014 |
20140260258 | SYSTEM FOR PROVIDING A WORKING FLUID TO A COMBUSTOR - A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage. | 09-18-2014 |
20140260259 | MULTI-ZONE COMBUSTOR - A multi-zone combustor is provided and includes a pre-mixer configured to output a first mixture to a primary zone of a combustor section and a stepped center body disposable in an annulus defined within the pre-mixer. The stepped center body includes an outer body configured to output at a first radial and axial step a second mixture to a secondary zone of the combustor section and an inner body disposable in an annulus defined within the outer body and configured to output at a second radial and axial step a third mixture to a tertiary zone of the combustor section. | 09-18-2014 |
20140325989 | Combustor with Fuel Staggering for Flame Holding Mitigation - 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. | 11-06-2014 |
20150107255 | TURBOMACHINE COMBUSTOR HAVING AN EXTERNALLY FUELED LATE LEAN INJECTION (LLI) SYSTEM - A turbomachine combustor assembly includes a combustor including a combustor body extending from a head end to a second end through a combustion zone. At least one injector is configured and disposed to introduce a first combustible fluid into the combustion zone at the head end of the combustor body. At least one late lean injector (LLI) is configured and disposed to introduce a second combustible fluid downstream of the first combustible fluid. An external fluid delivery system is fluidically connected to the at least one LLI. The external fluid delivery system includes at least one combustible fluid delivery conduit that extends from a first end fluidically connected to the LLI to a second end external to the turbomachine combustor assembly. The second end is configured and disposed to deliver the second combustible mixture to the LLI. | 04-23-2015 |
20160123596 | COMBUSTOR WITH AXIAL STAGING FOR A GAS TURBINE ENGINE - A combustor a gas turbine engine includes an axial fuel injection system in communication with a combustion chamber, the axial fuel injection system operable to supply between about 10%-35% of a combustion airflow. A radial fuel injection system communicates with the combustion chamber downstream of the axial fuel injection system, where the radial fuel injection system is operable to supply between about 30%-60% of the combustion airflow. A multiple of dilution holes are in communication with a combustion chamber downstream of said radial fuel injection system, where the multiple of dilution holes are operable to supply between about 5%-20% of the combustion airflow. | 05-05-2016 |
20160123597 | 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 combustor arrangement includes acentral lance body arranged inside the flow path and extending from the first burner through the first combustion chamber into the mixer and into the second burner, wherein the lance body includes a fuel duct for providing fuel for the first burner and/or for the second burner. | 05-05-2016 |