Patent application number | Description | Published |
20100319350 | Flashback Resistant Fuel Injection System - A fuel injector assembly includes a fuel injector that provides fuel to be mixed with air for ignition in a combustor. The fuel injector assembly includes a fuel shroud and a plurality of spanning members. The spanning members are spaced circumferentially on the fuel shroud between the fuel shroud and a base plate assembly, which supports the fuel injector assembly within the combustor. The spanning members space the fuel shroud from the base plate assembly such that an annular gap is formed therebetween. The gap permits a flow of purge air therethrough to be mixed with compressed air entering the fuel shroud and with fuel provided by the fuel injector. The spanning members comprise elongate members having upstream ends that are circumferentially offset from opposed downstream ends so that the spanning members provide tangential velocity to the purge air flowing through the annular gap. | 12-23-2010 |
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 |
20110302924 | COOLED CONDUIT FOR CONVEYING COMBUSTION GASES - A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume. | 12-15-2011 |
20120006028 | DAMPING RESONATOR WITH IMPINGEMENT COOLING - A resonance chamber ( | 01-12-2012 |
20120198854 | RESONATOR SYSTEM WITH ENHANCED COMBUSTOR LINER COOLING - A combustor liner has a plurality of resonators formed thereon. Each resonator has a radially outer wall and at least one side wall. The outer wall can be free of holes. Each resonator has an inner cavity defined between the outer wall, the at least one side wall and the outer peripheral surface of the liner. The at least one side wall of each resonator surrounds a subset of a plurality of holes that extend substantially radially through the liner. A plurality of cooling passages extends generally longitudinally within the liner. Each cooling passage has an inlet in fluid communication with the exterior of the liner and an outlet in fluid communication with the inner cavity of a respective one of the resonators. A coolant, such as compressor air, can enter and flow along the cooling passages to thereby cool the liner and purge the inner cavity of the resonator. | 08-09-2012 |
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 |
20130133330 | DEVICE TO LOWER NOx IN A GAS TURBINE ENGINE COMBUSTION SYSTEM - An emissions control system for a gas turbine engine including a flow-directing structure ( | 05-30-2013 |
20130219853 | MID-SECTION OF A CAN-ANNULAR GAS TURBINE ENGINE WITH AN IMPROVED ROTATION OF AIR FLOW FROM THE COMPRESSOR TO THE TURBINE - A midframe portion ( | 08-29-2013 |
20140208757 | 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. | 07-31-2014 |
20140338304 | AIR REGULATION FOR FILM COOLING AND EMISSION CONTROL OF COMBUSTION GAS STRUCTURE - A gas turbine engine compressed air flow control arrangement, including: a combustion gas structure having an acceleration geometry ( | 11-20-2014 |
20150020498 | COOLING COVER FOR GAS TURBINE DAMPING RESONATOR | 01-22-2015 |
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 |
20150082794 | APPARATUS FOR ACOUSTIC DAMPING AND OPERATIONAL CONTROL OF DAMPING, COOLING, AND EMISSIONS IN A GAS TURBINE ENGINE - Acoustic damping resonators ( | 03-26-2015 |