NECESSARY PRESSURE AND FUEL CONSUMPTION IN THE AIRCRAFT GAS TURBINE ENGINE FUEL SYSTEM DEVELOPMENT METHOD Russian patent published in 2018 - IPC F02C7/236 

FIELD: engines and pumps.

SUBSTANCE: invention relates to the necessary pressure and fuel consumption in the aircraft gas turbine engine fuel system development method. Pressure and fuel consumption development method in the aircraft gas turbine engine fuel system containing the electrically driven fuel pump, mechanically driven from the drives box fuel pump, fuel meter / distributor, controller, sensors, consisting in the fact, that enabling the fuel system and the gas turbine engine operation by supplying fuel from the electrically driven pump for up to 40 % of the gas turbine engine maximum rotor speed, gradually reducing the electric driven fuel pump rotation speed, and / or opening the fuel bypass from the electric driven pump outlet to the fuel system input, at the gas turbine engine rotor rotation speeds of more than 40 % enabling the necessary fuel consumption by supply from the mechanical driven fuel pump and from the electric driven fuel pump, at the electric driven fuel pump operation stages in the fuel system, in addition to the required fuel consumption in the combustion chamber, they additionally enabling the necessary pressure and fuel consumption for the hydraulic actuating units and fuel distribution units operation, after the gas turbine engine start-up completion and when the gas-turbine engine reaches the idle power mode, the electrically driven pump is transferred to the stand-by mode with reduced head on or switched off, ground idle power mode and all engine modes with the gas turbine engine rotor and the power-driven fuel pump drive shaft speeds of more than in the idle power mode are enabled by the power-driven fuel pump operation to supply the required fuel consumption into the gas turbine engine combustion chamber and develop the necessary fuel consumption and pressure for the hydraulic actuators operation, in addition, in the gas turbine engine operating modes with the gas turbine engine rotor speeds above 40 % and the occurrence of conditions with insufficient fuel pressure at the mechanical driven fuel pump inlet or outlet, as well as fuel temperature below +10 °C at the mechanical driven pump inlet turning on and / or increasing the rotor speed for the electrically driven fuel pump and maintaining the fuel pressure or temperature at the required level.

EFFECT: present invention allows to eliminate restrictions on the fuel flow and pressure at the gas turbine engine low rotation speed, reduce the fuel pre-heating amount from the fuel pump with unregulated performance (mechanical drive) in the gas turbine engine main modes with low fuel consumption, increase the gas turbine engine fault tolerance in terms of the “spontaneous shutdown” functional failure, enable conditions for the fuel pumps long-term life achievement, to obtain the fuel pumps optimal weight and size parameters.

1 cl, 1 dwg