Abstract: A burner arrangement includes a carrier and at least two burners which are mounted on the carrier in a flow direction Each burner includes a cylindrical housing having a lance which is arranged centrally therein and having a fuel duct and which is supported on the housing via swirl blades. An attachment is arranged on the side leading to a combustion chamber At least one fuel nozzle is disposed in the attachment and is connected to the fuel duct. The at least two fuel nozzles of the at least two burners have a different functional characteristic and/or spray form, and the at least two fuel nozzles of the at least two burners with a different functional characteristic and/or spray form include at least one full jet nozzle and at least one pressure swirl nozzle.

Abstract: A burner assembly for a gas turbine is provided. The burner assembly has a combustor, a centrally arranged pilot burner and plurality of main burners surrounding the pilot burner. Each main burner has a cylindrical housing having a lance which is centrally arranged therein and has a fuel channel for liquid fuel. The lance is supported on the housing by swirl blades and an attachment is arranged on the lance in the direction of the combustor. The liquid fuel nozzle is arranged in the attachment downstream of the swirl blades and connected to the fuel channel. For the improved mixing of the fuel with the air, the liquid fuel nozzle is designed as a full jet nozzle and the full jet nozzle has a length and a diameter, the ratio of the length to the diameter is at least 1.5.

Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

Abstract: A burner for stabilizing the combustion of a gas turbine is provided. The burner includes a combustion chamber and a plurality of nozzles opening out into the combustion chamber wherein fluid is introduced into the combustion chamber by the nozzles in the form of a fluid jet, wherein the fluid is burned in the combustion chamber to fatal a hot gas, wherein an annular gap is provided in the case of at least one nozzle for feeding the fluid to the nozzle at a nozzle inlet, wherein a preheater is provided for heating the fluid before entering the nozzle, wherein the preheater is a pre-burner with or without a combustion chamber, and wherein the pre-burner with or without a combustion chamber is arranged in the annular gap.

Abstract: A burner of a gas turbine including a reaction chamber and a plurality of jet nozzles opening into the reaction chamber is provided. Fluid is injected through an outlet into the reaction chamber by the jet nozzles using of a fluid stream wherein the fluid is burned into hot gas in the reaction chamber. An annular gap is disposed about the fluid stream for at least one jet nozzle so that a part of the hot gas is drawn out of the reaction chamber and flows opposite the fluid flow direction into the annular gap and is mixed with the fluid stream within the jet nozzle. The ring gap is formed by means of an insert tube, and wherein the insert rube includes a thickening at the upstream end. A method for stabilizing the flame of such a burner of a gas turbine is also provided.

Abstract: A fuel line system for a gas turbine and a method for purging the same is provided. Parts of the line system may be purged using a comparatively low quantity of purging medium.

Abstract: A method for operating a burner comprising a burner axis and at least one jet nozzle is provided. The nozzle or nozzles include a central axis, a jet nozzle outlet, a wall that runs in a radial direction starting from the central axis and that faces the burner axis and a volumetric fluid flow that includes a fuel and flows through the jet nozzle or nozzles to the jet nozzle outlet. An air film is formed at the jet nozzle outlet between the volumetric fluid flow including the fuel and the wall that faces the burner axis by means of air that is injected into the jet nozzle or nozzles along the wall that faces the burner axis.

Abstract: A method for reducing self-induced flame oscillations is provided. In a first fluid mass flow flowing through a jet nozzle from a fluid inlet opening to a fluid outlet opening, a second fluid mass flow is injected on an axial position of the jet nozzle positioned downstream from the fluid inlet opening. One fluid mass flow includes air, and the other fluid mass flow includes a fuel. A second method for reducing self-induced flame oscillations is also provided. In a first fluid mass flow flowing through a jet nozzle from a fluid inlet opening to a fluid outlet opening, a second fluid mass flow is injected on a radial position of the jet nozzle in relation to the circumference of the jet nozzle. One mass flow includes air and the other fluid mass flow includes a fuel. Burners which ensure the execution of the method are also provided.

Abstract: A burner incorporating a pilot cone and a mounting insert is provided. The pilot cone is constructed as a pilot cone assembly which is decoupled from the mounting insert. Further, an operating method for increasing the service life of a burner which incorporates a pilot cone assembly and a mounting insert is provided. The pilot cone assembly has a cone side and incorporates at least one further side where the further side is arranged to be essentially parallel to one of the sides of the mounting insert and spaced apart from it, so that between the further side and the side of the mounting insert there is a defined gap. In an operation of the burner, the gap is significantly reduced by the thermal expansion in at least at one point of contact between the further side and the side of the mounting insert. Finally, an assembly method is provided.

Abstract: A gas-turbine burner having a plurality of main swirl generators, each having an inlet flow opening formed by the main swirl generator edge, is provided. In order to achieve a uniform flow of combustion air through the main swirl generator, the gas-turbine burner has an inlet-flow guide means with a flow guide surface which runs from one of the inlet-flow openings to an adjacent inlet-flow opening, to which the main swirl generator edges which form the inlet-flow openings are connected, and the flow guide surface widens from there radially upwards. The main swirl generators are central-symmetrically arranged around a pilot burner and the flow guide surface runs radially outside the main swirl generators.

Abstract: A method for stabilizing the flame of a premixing burner, comprising a reaction chamber containing a fluid is provided. The method includes injecting an air-fuel mixture into the reaction chamber at a speed that is different from that of the fluid present in the reaction chamber, adjusting the speed such that vortices form at the boundary between the air-fuel mixture and the surrounding fluid. A premixing burner including a reaction chamber and at least one premixing spray nozzle opening into the reaction chamber is also provided. The premixing burner injects an air-fuel mixture into the reaction chamber at a speed that is different from that of the surrounding fluid, the speed being adjusted such that vortices from at the boundary between the air-fuel mixture and the surrounding fluid.