Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A method for monitoring a flame in a combustion chamber comprising a wall with an outer side is provided, wherein the radiation which is emitted from a part of the outer side of the wall is optically detected by a sensor. Furthermore, a burner is provided, especially for use in a gas turbine. The burner comprises a wall section with an inner side, which shows towards a combustion zone, and an outer side. The burner further comprises a sensor for optically detecting the radiation emitted from the outer side of said wall section.

Abstract: 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.

Abstract: 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.

Abstract: Disclosed is a ring-shaped fuel injector having an inner diameter, an outer diameter and a height, a fuel groove arranged in a face side of the ring, and at least one fuel injection opening arranged on the ring and connected to the fuel groove.

Abstract: A liquid fuel injection nozzle to supply atomized droplets of fuel to a combustion chamber arrangement in a gas turbine engine combustion system. The fuel droplets leave the passage through its upper end defined by an annular sharp edge of a tubular electrode which can be electrostatically charged for the sharp edge to impart electrostatic charge to the fuel droplets as they pass the edge.

Abstract: A gas turbine engine includes a combustion main chamber into which opens one end of an upstream combustion pre-chamber having a burner face at its opposite end. A swirler assembly has a plurality of generally tangentially extending swirler vanes circumferentially spaced by passages disposed about a center and along which combustion air follows radially inward paths into the pre-chamber. Each passage is provided with a respective liquid fuel injection nozzle including an electrode to be electrostatically charged so each injection nozzle can impart electrostatic charge to droplets of fuel emerging from the nozzles to travel with the combustion air into the pre-chamber. Walls of the passages comprise electrodes which can be charged to the same polarity as the charged fuel.

Abstract: A gas turbine engine includes a combustion main chamber into which opens one end of an upstream combustion pre-chamber having a burner face at its opposite end. A swirler assembly has a plurality of generally tangentially extending swirler vanes circumferentially spaced by passages disposed about a center and along which combustion air follows radially inward paths into the pre-chamber. Each passage is provided with a respective liquid fuel injection nozzle including an electrode to be electrostatically charged so each injection nozzle can impart electrostatic charge to droplets of fuel emerging from the nozzles to travel with the combustion air into the pre-chamber. Walls of the passages comprise electrodes which can be charged to the same polarity as the charged fuel.

Abstract: A liquid fuel injection nozzle to supply atomized droplets of fuel to a combustion chamber arrangement in a gas turbine engine combustion system. The fuel droplets leave the passage through its upper end defined by an annular sharp edge of a tubular electrode which can be electrostatically charged for the sharp edge to impart electrostatic charge to the fuel droplets as they pass the edge.