| 摘要 |
The present invention relates to a combustion chamber of a gas turbine working on liquid fuel, comprising a tubular enclosure (2) having at least one pressurized air inlet, a liquid fuel injection means (6) positioned on or in proximity to the longitudinal axis XX' of the tubular enclosure, an outlet to the turbine. According to the invention said fuel injection means (6) comprises a series of orifices (62) arranged so as to create separate fuel jets, said jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30° and 60° at the vertex thereof, said chamber comprises at least two types of pressurized air inlets placed close to each other, the first one (7) taking in the air helically around the longitudinal axis of the combustion chamber, the second air inlet (8) being tangential to enclosure (2) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel. The assembly preferably works at a pressure ranging between 2 and 30 bars and with a fuel/air ratio ranging between 0.4 and 0.8.
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