FUEL SYSTEM OF MAIN COMBUSTION CHAMBER OF GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C7/22 F02C9/26 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine building, particularly, to fuel supply system of main combustion chamber of gas turbine engine and fuel manifold for spraying of liquid fuel. Invention objective is to preserve prolonged burning at one or several duty nozzles at cutoffs of fuel supply to collector for further combustion recovery without use of ignition system. Set task is solved by the fact that in the collector design there is an open (one or more) centrifugal double-flow open-type nozzle with a protective cap, which at cutouts of fuel supply to collector switches to autonomous power supply with low fuel consumption, which ensures maintenance of optimum coefficient of excess air supplied to nozzle end through channels of anti-carbon cap. At that, combustion zone is arranged by swirling of this air directly behind nozzle end.

EFFECT: long-term maintenance of combustion in the zone of the duty nozzle, which ensures recovery of combustion in the main combustion chamber at sharp drops of fuel consumption, operation of the anti-missile system, start-up at autorotation modes, et cetera, without use of ignition system.

3 cl, 2 dwg