초록 ▼

A combustion chamber of a gas turbine working on liquid fuel includes 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, and an outlet to the turbine. The fuel inj

A combustion chamber of a gas turbine working on liquid fuel includes 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, and an outlet to the turbine. The fuel injection means (6) includes a series of orifices (62) arranged so as to create separate fuel jets, the jets being arranged in the direction of the generatrices of a cone with an angle ranging between 30.degree. and 60.degree. at the vertex thereof. The chamber includes 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.

대표청구항 ▼

1. A combustion chamber of a gas turbine working on liquid fuel, comprising a tubular enclosure (2) having at least one air inlet, a liquid fuel injection means (6) producing fuel jets and being positioned on or in proximity to the longitudinal axis (XX') of the tubular enclosure, an outlet to the t

1. A combustion chamber of a gas turbine working on liquid fuel, comprising a tubular enclosure (2) having at least one air inlet, a liquid fuel injection means (6) producing fuel jets and being positioned on or in proximity to the longitudinal axis (XX') of the tubular enclosure, an outlet to the turbine, a first pressurized air inlet (7) connected to a source of pressurized air and not being connected to a source of liquid fuel and taking in the air helically around the longitudinal axis of the combustion chamber, a second pressurized air inlet (8) connected to a source of pressurized air and not being connected to a source of liquid fuel and taking in the air tangentially to enclosure (2) so as to create, around the fuel jets, counterrotating flows intended to improve mixing of the air and of said fuel, wherein said fuel injection means (6) comprises a series of orifices arranged so as to create separate fuel jets, said jets being positioned along the generatrices of a cone with an angle ranging between 30.degree. and 60.degree. at the vertex thereof, in that the assembly operates at a pressure ranging between 2 and 30 bars and with a global mixture strength ranging between about 0.4 and 0.8, and in that the residence time of the fluids in enclosure (2) is less than 50 milliseconds.