Abstract: In the combustion chamber of a gas turbine, an air distribution chamber (19) and a combustion space (7) are locationally separated from one another within the combustion chamber shell (1). A multiplicity of tubular elements (2) are located between the distibution chamber and the combustion space, in which elements a premixing and pre-evaporation of the fuel oil supplied via the premixing nozzles (15') and/or a premixing of the fuel gas supplied through the premixing nozzles (15") takes place with compressor air. Each tubular element (2) is provided with a flameholder (3) in the direction towards the combustion space (7). A diffusion nozzle (8) for fuel directed into the combustion space (7) is located within the flameholder. In operation on load, only a small part of the fuel supplied to each element (2) is burned by means of the diffusion nozzle (8), the major proportion, on the other hand, being burnt by means of the premixing nozzles (15' of 15").

Abstract: This invention relates to improvements in the art of liquid fuel combustion and, more particularly, concerns a method and apparatus for the controlled gassification of liquid fuels, the thorough premixing of the then gassified fuel with air and the subsequent gas-phase combustion of the mixture to produce a flame substantially free of soot, carbon monoxide, nitric oxide and unburned fuel.

Abstract: This invention relates to improvements in the art of liquid fuel combustion and, more particularly, concerns a method and apparatus for the controlled gassification of liquid fuels, the thorough premixing of the then gassified fuel with air and the subsequent gas-phase combustion of the mixture to produce a flame substantially free of soot, carbon monoxide, nitric oxide and unburned fuel.