Patent application number | Description | Published |
20100071376 | Combustor Assembly in a Gas Turbine Engine - A combustor assembly in a gas turbine engine. The combustor assembly includes a combustor device coupled to a main engine casing, a first fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner disposed radially inwardly from the flow sleeve. The first fuel injection system provides fuel that is ignited with the pressurized air creating first working gases. The intermediate duct is disposed between the liner and the transition duct and defines a path for the first working gases to flow from the liner to the transition duct. An intermediate duct inlet portion is associated with a liner outlet and allows movement between the intermediate duct and the liner. An intermediate duct outlet portion is associated with a transition duct inlet section and allows movement between the intermediate duct and the transition duct. | 03-25-2010 |
20100071377 | Combustor Apparatus for Use in a Gas Turbine Engine - A combustor apparatus for use in a gas turbine engine. The combustor apparatus includes a liner, a flow sleeve, and a fuel injection system. The liner includes an inner volume, wherein a portion of the inner volume defines a main combustion zone. The flow sleeve receives compressed air, is positioned radially outward from the liner, and includes a forward end and an aft end. The fuel injection system is coupled to the flow sleeve and provides fuel into the inner volume of the liner downstream from the main combustion zone. The fuel injection system includes a fuel manifold and a fuel dispensing structure. The fuel manifold is coupled to the flow sleeve and includes a cavity for receiving fuel. The fuel dispensing structure is associated with the cavity and distributes fuel from the cavity to the liner inner volume. | 03-25-2010 |
20100077760 | Flex-Fuel Injector for Gas Turbines - A fuel injector ( | 04-01-2010 |
20110067402 | Fuel Nozzle Assembly for Use in a Combustor of a Gas Turbine Engine - A fuel nozzle assembly for use in a combustor apparatus of a gas turbine engine. An outer housing of the fuel nozzle assembly includes an inner volume and provides a direct structural connection between a duct structure and a fuel manifold. The duct structure defines a flow passage for combustion gases flowing within the combustor apparatus. The fuel manifold defines a fuel supply channel therein in fluid communication with a source of fuel. A fuel injector of the fuel nozzle assembly is provided in the inner volume of the outer housing and defines a fuel passage therein. The fuel passage is in fluid communication with the fuel supply channel of the fuel manifold for distributing the fuel from the fuel supply channel into the flow passage of the duct structure. | 03-24-2011 |
20110091829 | MULTI-FUEL COMBUSTION SYSTEM - The present invention explains a multi-fuel combustion system. It consist of a combustor basket adapted to combust at least two type of fuels. The combustor basket has got a circumferential wall comprising a plurality of openings. The combustion system further has a first conduit adapted to provide a first type of fuel directly to the combustor basket, a second conduit adapted to provide a second type of fuel directly to the combustor basket and a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel through the openings into the combustor basket. | 04-21-2011 |
20110203284 | CIRCUMFERENTIAL BIASING AND PROFILING OF FUEL INJECTION IN DISTRIBUTION RING - An annular fluid distribution device ( | 08-25-2011 |
20110203285 | BURNER ARRANGEMENT - 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. | 08-25-2011 |
20110289928 | AIR/FUEL SUPPLY SYSTEM FOR USE IN A GAS TURBINE ENGINE - A fuel injector for use in a gas turbine engine combustor assembly. The fuel injector includes a main body and a fuel supply structure. The main body has an inlet end and an outlet end and defines a longitudinal axis extending between the outlet and inlet ends. The main body comprises a plurality of air/fuel passages extending therethrough, each air/fuel passage including an inlet that receives air from a source of air and an outlet. The fuel supply structure communicates with and supplies fuel to the air/fuel passages for providing an air/fuel mixture within each air/fuel passage. The air/fuel mixtures exit the main body through respective air/fuel passage outlets. | 12-01-2011 |
20110296839 | Self-Regulating Fuel Staging Port for Turbine Combustor | 12-08-2011 |
20120137691 | Gas turbine assembly and method therefor - An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange. | 06-07-2012 |
20120260666 | MULTI-FUEL COMBUSTION SYSTEM - A multi-fuel combustion system is provided. The system includes a combustor basket adapted to combust at least two type of fuels. The combustor basket includes a circumferential wall with a plurality of openings. The combustion system further includes a first conduit adapted to provide a first type of fuel directly to the combustor basket and a second conduit adapted to provide a second type of fuel directly to the combustor basket. The combustion system also may include a third conduit adapted to inject at least one of the first type of fuel and the second type of fuel through the openings into the combustor basket. | 10-18-2012 |
20130055720 | INTERFACE RING FOR GAS TURBINE NOZZLE ASSEMBLIES - A gas turbine combustor assembly including a combustor liner and a plurality of fuel nozzle assemblies arranged in an annular array extending within the combustor liner. The fuel nozzle assemblies each include fuel nozzle body integral with a swirler assembly, and the swirler assemblies each a bellmouth structure to turn air radially inwardly for passage into the swirler assemblies. A radially outer removed portion of each of the bellmouth structures define a periphery diameter spaced from an inner surface of the combustor liner, and an interface ring is provided extending between the combustor liner and the removed portions of the bellmouth structures at the periphery diameter. | 03-07-2013 |
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 |
20130074501 | COMBUSTOR RESONATOR SECTION WITH AN INTERNAL THERMAL BARRIER COATING AND METHOD OF FABRICATING THE SAME - A combustor ( | 03-28-2013 |
20130074946 | CAST MANIFOLD FOR DRY LOW NOx GAS TURBINE ENGINE - A casting ( | 03-28-2013 |
20130104554 | BURNER ASSEMBLY | 05-02-2013 |
20130174560 | COMBUSTOR ASSEMBLY IN A GAS TURBINE ENGINE - A combustor assembly in a gas turbine engine includes a combustor device, a fuel injection system, a transition duct, and an intermediate duct. The combustor device includes a flow sleeve for receiving pressurized air and a liner surrounded by the flow sleeve. The fuel injection system provides fuel to be mixed with the pressurized air and ignited in the liner to create combustion products. The intermediate duct is disposed between the liner and the transition duct so as to define a path for the combustion products to flow from the liner to the transition duct. The intermediate duct is associated with the liner such that movement may occur therebetween, and the intermediate duct is associated with the transition duct such that movement may occur therebetween. The flow sleeve includes structure that defines an axial stop for limiting axial movement of the intermediate duct. | 07-11-2013 |
20130327045 | GAS TURBINE COMBUSTION CHAMBER WITH FUEL NOZZLE, BURNER WITH SUCH A FUEL NOZZLE AND FUEL NOZZLE - A gas turbine combustion chamber includes a fuel nozzle with a cylindrical nozzle tube, in which a fluid flows, and a convexly formed nozzle cover, which is arranged downstream of the nozzle tube. The nozzle cover has a central point and a plurality of through-openings through which the fluid leaves the nozzle tube. The through-openings are arranged at different radial distances from the central point at two circular lines. | 12-12-2013 |
20140130502 | GAS TURBINE ASSEMBLY AND METHOD THEREFOR - An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange. | 05-15-2014 |
20150047361 | NOZZLE WITH MULTI-TUBE FUEL PASSAGEWAY FOR GAS TURBINE ENGINES - A pilot fuel nozzle for a combustor includes an igniter forming a central body extending along a longitudinal center of the nozzle. A nozzle tip includes a plurality of circumferentially spaced fuel passages and a plurality of circumferentially spaced air passages extending to an outer side of the nozzle tip. The central body extends through a center of the nozzle tip for producing a spark to ignite a fuel/air mixture adjacent to the nozzle tip. A plurality of fuel tubes extend along the central body, each of the fuel tubes having an outlet end engaged on the nozzle tip for delivery of fuel from the nozzle tip into a combustion chamber of the combustor An outer sleeve surrounds the fuel tubes and defines an annular space in fluid communication with the air passages of the nozzle tip between the outer sleeve and the central body | 02-19-2015 |