GAS TURBINE PLANT COMBUSTION CHAMBER Russian patent published in 2008 - IPC F23R3/38 

FIELD: engines and pumps.

SUBSTANCE: gas turbine combustion chamber incorporates a compressor, a compressor turbine, a combustion chamber with rotary nozzle fitted on the turbo compressor rotor. The nozzle contains a fixed taper disk with an annular manifold and radial pipes to feed fuel into the combustion zone. The radial pipes are equidistant along the circumference. The nozzle incorporates a rotary tapered disk aligned with the fixed one. The rotary disk tapered surface facing the fixed disk accommodates multithread screw channels formed by the screw heckles. The latter are made inclined towards the rotation side with the sharp cutting edge and fluting plane nearby the heckle base.

EFFECT: higher efficiency of the gas turbine plant, fuller combustion and lower pollution.

3 cl, 3 dwg