FUEL FLOW CONTROL SYSTEM TO GAS TURBINE ENGINE Russian patent published in 2019 - IPC F02C9/26 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine building and can be used in electronic-hydromechanical systems for automatic control of aircraft GTE to control fuel consumption in aircraft. In the fuel flow control system of the gas turbine engine, which includes the first and the second combustion chamber headers, the electronic controller connected to the sensors unit, in series connected the first electrohydraulic booster, the first fuel batcher, first pressure difference valve, series-connected second electrohydraulic booster, second fuel dispenser and second pressure difference valve, electrohydraulic booster are connected to electronic controller, second inputs of proportioners and second inputs of differential valves are connected to fuel pump, position sensors of proportioning elements of dispensers, connected to electronic controller, according to present invention, system is additionally equipped with first and second electrohydraulic valves controlled by electronic regulator and first and second fuel distributors into combustion chamber manifolds, wherein each fuel distributor is connected to first and second headers, first fuel distributor by its input is connected to first pressure difference valve output, second distributor is connected to second differential pressure valve outlet. First hydraulic valve output is connected to first differential pressure valve and second fuel distributor. Second hydraulic outlet is connected to second differential valve and first fuel distributor.

EFFECT: higher reliability of fuel dosing system, higher completeness of fuel combustion and reduced harmful emissions.

1 cl, 1 dwg, 1 tbl