Patent application number | Description | Published |
20080315010 | Fuel Injector - A fuel injector comprising: a fuel supply conduit for conveying fuel from a base end of the fuel injector to a tip end of the injector; a nozzle at the tip end of the injector for injecting the fuel into a combustion chamber; thermal conductor means for conducting heat from said nozzle at the tip end of the injector to the base end of the injector to cool the nozzle; and a housing for said fuel supply conduit, said nozzle and said thermal conductor means, wherein said thermal conductor means is thermally insulated from said fuel supply conduit between said tip and base ends of the injector. | 12-25-2008 |
20090025395 | Swirler for Use in a Burner of a Gas Turbine Engine - Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a plurality of vanes arranged in a circle, flow slots being defined between adjacent vanes in the circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of fuel and air travelling along each flow slot from its inlet end to its outlet end such that the swirler provides a swirling mix of the fuel and air, at least one vane having an edge adjacent an inlet end of a flow slot configured to generate within the flow slot one or more flow vortices that extend along the slot thereby to enhance mixing of the fuel and air travelling along the slot. | 01-29-2009 |
20090117502 | Combustor and Method of Operating a Combustor - A combustor comprises in flow series a burner, a transition piece and a combustion chamber being of larger diameter than the transition piece, the combustion chamber being connected to the transition piece via a dome portion. In the dome portion are located air injection openings. A method of operating the combustor comprises the stop of introducing air from the dome portion by means of air jets. | 05-07-2009 |
20090139242 | Burners for a gas-turbine engine - A burner for a gas-turbine engine has a frustoconical burner shell, at least two swirler arrangements, which are connected to the shell and are spaced apart around the circumference of the shell between its two ends, and a combustion chamber disposed downstream of a wider end of the shell. Each of the swirler arrangements includes an air swirler and a pre-combustion chamber disposed downstream of the air swirler, and a longitudinal axis of each swirler arrangement intersects a line parallel to, and spaced apart from, the longitudinal axis of the shell. The swirler arrangements are preferably connected to the shell at the same axial point. | 06-04-2009 |
20090249793 | Apparatus for Modifying the Content of a Gaseous Fuel - There is described an apparatus for modifying the content of a gaseous fuel comprising: a supply of the gaseous fuel; a supply of an oxidant; and a combustion device for utilising the oxidant to partially combust a first proportion of the fuel thereby to produce products of the partial combustion including intermediate combustion products, the products of the partial combustion mixing with the remaining proportion of fuel not partially combusted thereby to provide the modified fuel, wherein the partial combustion is controlled so as to provide the intermediate combustion products required to produce a predetermined modified fuel. | 10-08-2009 |
20090272117 | Burner - The invention relates to a burner, in particular a gas turbine burner, comprises: at least one swirler, the swirler having at least one air inlet opening, at least one air outlet opening positioned downstream to the air inlet opening and at least one swirler air passage extending from the at least one air inlet opening to the at least one air outlet opening which is delimited by swirler air passage walls, the air passage walls comprising downstream wall sections adjoining the at least one air outlet opening; and a fuel injection system which comprises fuel injection openings arranged in at least one swirler air passage wall so as to inject fuel into the swirler air passage; in which at least the downstream section of one air passage wall is corrugated. | 11-05-2009 |
20090277179 | SWIRLER PASSAGE AND BURNER FOR A GAS TURBINE ENGINE - A swirler passage is provided for mixing fuel and compressor air with at least two side walls; at least first and second conduits arranged inside at least one of the at least two side walls, the first conduit forming a fuel gas conduit and the second conduit forming an air conduit, the fuel gas conduit connected to a gas fuel supply and the air conduit connected to an air supply; a tube connected to the fuel gas conduit and entirely traversing the air conduit inside the side wall; a fluid passage connected to the air conduit and surrounding the tube; at least one fuel outlet opening of the tube arranged on the side wall; and at least one air outlet opening of the fluid passage arranged on the side wall and surrounding the fuel outlet opening. | 11-12-2009 |
20090301092 | Burners for a gas turbine engine - A burner for a gas-turbine engine including a swirler and a combustion chamber is provided. The swirler includes a plurality of vanes arranged in a circle, each adjacent pair of vanes defining a flow slot for the flow of air and fuel into the swirler, the air and fuel is mixed and supplied in swirling form to the combustion chamber. The swirler can also include a partitioning device which divides the flow of air along each flow slot into two air flows. One side of the partitioning device has a fuel-supply port for supplying fuel to one of the two air flows. The relevant air flow causes fuel supplied to the fuel-supply port to form a film of fuel over the relevant side of the partitioning device. The film leaves the relevant side of the partitioning device in a region of high shear between adjacent flows in the burner. | 12-10-2009 |
20090320485 | Swirler for Use in a Burner of a Gas Turbine Engine - Disclosed is a swirler for use in a burner of a gas turbine engine, the swirler comprising a pluralkity of vanes arranged in a circle, flow slots being defined between adjacent vanes in a circle, each flow slot having an inlet end and an outlet end, in use of the swirler a flow of air and fuel traveling along each flow slot fom its inlet end to its outlet end such that the swirler provides a swirling mix of the air and fuel, at least one vane being configured to generate a flow vortex that extends from an edge of the vane adjacent an outlet end of a flow slot to within the swirling mix thereby to improve the mix of air and fuel in the swirling mix. | 12-31-2009 |
20100065663 | Fuel-Injector Nozzle - A nozzle for a fuel injector, in particular for a gas-turbine engine, is provided comprising a planar conductive electrode with a sharp edge forming an aperture, an upper insulation layer above the electrode and a lower insulation layer below the electrode, both insulation layers having apertures, and a swirler arrangement for creating a swirling action in liquid fuel introduced into the nozzle. The axis of swirl is generally perpendicular to the plane of the electrode. In use, the swirling fuel passes through the aperture of the lower insulation layer, the aperture of the conductive electrode and the aperture of the upper insulation layer. As the fuel passes through the aperture of the electrode, the electrode charges the swirling fuel, so that the nozzle supplies charged droplets of atomised fuel from an outlet orifice. The swirler arrangement may be a radial or axial swirler arrangement. | 03-18-2010 |
20100107644 | COMBUSTION PRE-CHAMBER - A combustion pre-chamber including an upstream end and a downstream end is provided. The combustion pre-chamber includes a transition channel formed by a wall, the wall extending between the upstream end and the downstream end, and at least one flow trip arranged on the wall and tapering in height and width to the downstream end. Also provided are a burner assembly including a combustion pre-chamber, and a gas turbine engine. | 05-06-2010 |
20100162710 | Pre-Mix Combustion System for a Gas Turbine and Method of Operating of operating the same - The invention is related to a gas turbine pre-mix combustion system comprising: at least one combustor with a combustor wall partly surrounding a combustion zone; at least one mixing duct including an air passage leading to an outlet opening being open towards the combustion zone; and one or more fuel injection openings leading into the air passage and connecting it to one or more fuel supply passages so as to allow the injection of fuel into air flowing through the air passage. The locations of at least two outlet openings or at least two sections of a single outlet opening and the orientation of downstream sections of the respective air passages or air passage are chosen such that fuel/air mixtures flowing out of the outlet openings or said sections of a single outlet opening show opposed flow paths so as to impinge on each other in the combustion zone. | 07-01-2010 |
20100175381 | SWIRLER - A swirler including a plate normal to a central axis of the swirler, a plurality of vane cross-sections arranged on the plate and radially positioned about the central axis and a plurality of twisted vanes is provided. The twisted part of each vane is twisted around the central axis wherein the cross section of the twisting vane is normal to the central axis. In one aspect, each vane has an essentially triangular cross section. | 07-15-2010 |
20100223932 | Gas Turbine Burner and Method of Mixing Fuel and Air in a Swirling Area of a Gas Turbine Burner - A gas turbine burner, comprising at least one swirler, the swirler having at least one air inlet opening, at least one air outlet opening positioned downstream to the air inlet opening and at least one swirler air passage extending from the at least one air inlet opening to the at least one air outlet opening which is delimited by swirler air passage walls; a fuel injection system which comprises fuel injection openings arranged in at least one swirler air passage wall so as to inject fuel into the swirler air passage; and an air injection system which comprises air injection openings arranged in at least one swirler air passage wall and positioned downstream of the fuel injection openings for injecting air into the swirler air passage. | 09-09-2010 |
20100293953 | COMBUSTOR FOR A GAS-TURBINE ENGINE - A combustor for a gas-turbine engine including a burner head, a combustion chamber disposed downstream of the burner head, a swirler for creating a swirling flow of air in the combustion chamber, and a fuel nozzle disposed in the burner head. The fuel nozzle is disposed giving rise to a first angle of exit of the fuel from a downstream face of the burner head of >±0° with respect to a longitudinal axis of the combustor, this first angle lying in a first plane passing through the longitudinal axis. The fuel also exits at a second angle from the downstream face of >±0° with respect to the first plane, the second angle lying in a second plane orthogonal to the first plane. | 11-25-2010 |
20110248726 | METHOD OF DETERMINING THE DIAMETER OF A HOLE IN A WORKPIECE - A method of determining the diameter of a hole extending from a surface of an electrically conducting workpiece into or through the workpiece | 10-13-2011 |