Patent application number | Description | Published |
20100154424 | Low cross-talk gas turbine fuel injector - A pilot assembly for a fuel injector of a gas turbine engine may include a longitudinal passageway having an outlet end. A mass flow in the longitudinal passageway may generally flow towards the outlet end during operation of the engine. The pilot assembly may also include a liquid fuel nozzle that is positioned to direct a mixture of liquid fuel and air near the outlet end, and a compressed air inlet that is configured to direct air compressed by a compressor of the engine to a compressor discharge pressure into the longitudinal passageway without a substantial loss of pressure. The longitudinal passageway may also include a flow restriction section. The flow restriction section may be a narrowed section of the longitudinal passageway, in which an upstream side of the flow restriction section may have compressed air at substantially the compressor discharge pressure and a downstream side may have air at a lower pressure and a higher velocity. The pilot assembly may further include a nozzle for injecting one of assist air or gaseous fuel into the longitudinal passageway. The nozzle may be positioned at the flow restriction section or on an upstream side of the flow restriction section to reduce cross-talk. | 06-24-2010 |
20120111016 | END-FED LIQUID FUEL GALLERY FOR A GAS TURBINE FUEL INJECTOR - A fuel injector for a gas turbine engine may include an injector housing extending along a longitudinal axis and configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a flow path for a fuel air mixture to the combustor extending longitudinally within the injector housing, and a gallery for liquid fuel encircling the flow path. The gallery may include a plurality of fuel spokes that are configured to deliver liquid fuel from the gallery to the flow path. The gallery may extend from a feed end to a terminal end that overlaps the feed end. The feed end may be a region where liquid fuel enters the gallery and the terminal end may be a region where the gallery terminates. | 05-10-2012 |
20120324900 | PHASE AND AMPLITUDE MATCHED FUEL INJECTOR - A fuel injector for a turbine engine may include a body member disposed about a longitudinal axis, and a barrel member located radially outwardly from the body member. The fuel injector may also include an annular passageway extending between the body member and the barrel member from a first end to a second end. The first end may be configured to be fluidly coupled to a compressor of the turbine engine and the second end may be configured to be fluidly coupled to a combustor of the turbine engine. The fuel injector may also include a perforated plate positioned proximate the first end of the passageway. The perforated plate may be configured to direct compressed air into the annular passageway with a first pressure drop. The fuel injector may also include at least one fuel discharge orifice positioned downstream of the perforated plate. The at least one fuel discharge orifice may be configured to discharge a fuel into the annular passageway with a second pressure drop. The second pressure drop may have a value between about the first pressure drop and about 1.75 times the first pressure drop. | 12-27-2012 |
20130168472 | METHOD AND APPARATUS FOR SWAGED LIQUID INJECTOR SPOKE - A liquid fuel injection spoke for a gas turbine engine. The liquid fuel injection spoke may include an inlet end and an outlet end. The liquid fuel injection spoke may further include a head located at the inlet end and a stem extending along a longitudinal axis from the head to the outlet end. The stem may define a fluid passageway therein. The head may include a cavity with an inner wall. The inner wall may include an annular protrusion. | 07-04-2013 |
20140026999 | EXHAUST DIFFUSER FOR A GAS TURBINE ENGINE HAVING CURVED AND OFFSET STRUTS - An exhaust diffuser having an outer turbine mounting interface, an outer exhaust collector mounting interface, an outer diffuser wall extending between the outer turbine mounting interface and the outer exhaust collector mounting interface, an inner turbine mounting interface, an inner exhaust collector mounting interface, an inner diffuser wall extending between the inner turbine mounting interface and the inner exhaust collector mounting interface, and a plurality of struts circumferentially distributed around the center axis and extending between the outer diffuser wall and the inner diffuser wall, wherein each of the plurality of struts is radially curved between the diffuser flow outer wall and the diffuser flow inner wall, respectively, and wherein the termination points of each strut is outer wall interface are radially offset from each other. | 01-30-2014 |
20140047813 | EXHAUST COLLECTOR WITH RADIAL AND CIRCUMFERENTIAL FLOW BREAKS - An exhaust collector having a radial inlet configured to receive exhaust gas in a radial direction, an outlet configured to deliver exhaust gas in and outlet direction, and an enclosure configured to collect the received exhaust gas into at least two circumferential counter flows, and route the collected exhaust gas to the outlet, wherein the enclosure includes a collected flow barrier configured to divide the collected exhaust gas from the exhaust gas received at the radial inlet, and a collected flow circumferential divider configured to form a physical barrier between at least a portion of the at least two circumferential counter flows. | 02-20-2014 |
20140137565 | COMBINATION AIR ASSIST AND PILOT GASEOUS FUEL CIRCUIT - When starting a dual fuel turbine engine on liquid fuel, a flow of air assist into a combined pilot gaseous fuel and air assist tube is supplied. The velocity of the flow of air assist is increased as it is expelled through an outlet of the tube. The flow of air assist is directed into a first end of a pilot injector barrel. Additional air is drawn into the first end of the pilot injector barrel from an enclosure containing both the first end of the pilot injector barrel and the tube outlet. Liquid pilot fuel is supplied at a second end of the pilot injector barrel, and this fuel is atomized by the flow of the air assist and additional air. The atomized pilot liquid fuel may then be combusted, | 05-22-2014 |
20140250907 | GAS TURBINE FUEL INJECTOR WITH METERING CAVITY - A fuel injector for a gas turbine engine may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery extending circumferentially around the flow path. The fuel gallery may be adapted to inject a liquid fuel into the flow path. The fuel injector may also include an annular casing positioned circumferentially around the fuel gallery to define an insulating chamber around the gallery. The fuel injector may also include an annular cover extending around the fuel injector to define a metering chamber. The fuel injector may further include one or more purge holes fluidly coupling the metering chamber to the insulating chamber, and one or more metering holes fluidly coupling the metering chamber to a volume exterior to the fuel injector. | 09-11-2014 |