| 摘要 |
FIELD: oil-and-gas industry; system for combustion of liquid and/or aeriform fuel in gas turbine. ^ SUBSTANCE: system for combustion of liquid and/or aeriform fuel in gas turbine contains the fire tube with the conical inlet diffusion, cylindrical median part and convergent outlet part, passing into nose piece or set of nozzles, the system for discharging the liquid or aeriform fuel, homogenisator, flow swirler and flame stabilizer are installed sequentially in front of combustion chamber. Nose piece or nozzle throat are made with critical profile. The flow swirler is installed between the homogenisator and conical diffusion of firing tube. The stabiliser is installed in the conical diffusion so as to make the ring-shaped channel with outlet to inlet square ratio Foutl/Finl related to its comparative length L/H, and not more than 0.3. The ratio of square of transverse profile Ft of cylindrical part of combustion chamber to the square Fcr of critical profile of nozzle Ft/ Fcr is more or equal to 36. The rotation angle of swirler's vanes is not less than 30°. ^ EFFECT: system provides the increased operating efficiency. ^ 1 dwg |
