PUMPING UNIT OF FUEL SUPPLY SYSTEM OF GAS TURBINE ENGINE OF AIRCRAFT Russian patent published in 2021 - IPC F02C7/22 

FIELD: aircraft engine building.

SUBSTANCE: invention relates to the field of aircraft engine building, in particular to the field of automatic control systems for fuel supply to a gas turbine engine of an aircraft, and allows to prevent overheating of fuel in the fuel supply system of a gas turbine engine while reducing the amount of fuel supply to 1%. The pumping unit of the fuel supply system of the gas turbine engine of the aircraft is made according to a two-stage scheme. The first stage contains the main fuel pump installed on the output shaft of the hydrodynamic torque converter connected to the shaft of the gas turbine engine, and the inner cavity of the hydrodynamic torque converter is hydraulically connected to the inlet of the main pump and to its pressure cavity, and the regulating body of the hydrodynamic converter is connected via a servo piston to the fuel supply regulator of the automatic engine control system. The second stage of the unit contains an additional pump in the form of a centrifugal impeller with a consumption power not exceeding 15 kW, mainly of an impeller type, installed on the input shaft of the hydrodynamic torque converter. The pressure chamber of the additional pump is connected to the outlet of the unit by means of a hydraulic channel with a shut-off check valve installed in it, while a shut-off check valve is also installed in the outlet of the main pump. The pressure chamber of the additional pump is also connected to the inner cavity of the converter through a throttle device.

EFFECT: invention performs its functions effectively.

1 cl, 1 dwg