FIELD: motors and pumps.
SUBSTANCE: invention relates to the field of operation of aircraft gas turbine engines (GTE) and can be used to control the supply of fuel to the main and / or afterburner combustion manifolds of the GTE. Multi-collector device for supplying fuel to the combustion chamber of a gas turbine engine comprising two or more fuel manifolds for supplying fuel to the fuel injectors, a dispenser. Between each two series-connected fuel manifolds, there is additionally a connecting line with a nozzle installed in it, with the possibility of a dosed flow of fuel from one manifold to another in the modes of starting the gas turbine engine.
EFFECT: proposed invention makes it possible to provide a consistent dosed filling of fuel collectors through connecting lines with jets, increase the reliability of the fuel supply device and the reliability of the engine start-up process in ground and flight conditions.
1 cl, 1 dwg
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