COMBUSTION CHAMBER Russian patent published in 1997 - IPC

FIELD: power, transport and chemical engineering; combustion chambers of gas turbines. SUBSTANCE: combustion chamber includes flame tube 1 and prechamber which consists of two circular coaxial blades swirlers 2 providing for opposite twisting of flow. Circular fuel main 3 mounted between swirlers is provided with fuel dispensing devices 4. Pilot burner 5 is mounted in near-axis zone of combustion chamber. Slit 8 is formed by circular ferrule 6 and circular deflector-shoulder 7; passage area of this slit is equal to 0.8 - 1.2 of total passage area of air swirlers 2. Air and fuel are fed in circular oppositely twisted jets to mixing prechamber formed by flame tube 1, circular ferrule 6 and deflector-shoulder 7 where air and fuel are mixed intensively. Then homogeneous fuel-and-air mixture is directed to near-axis are of combustion chamber by means of deflector-shoulder 7 through slit 8 at high velocity to exclude getting of flame into prechamber; in near-axis zone, mixture is ignited by means of flame of burner 5. EFFECT: avoidance of stoichiometric high-temperature zones in flame of homogeneously prepared fuel-and-air mixture which provides for reduced formation of nitric oxides. 1 dwg