GAS TURBINE ENGINE FUEL SUPPLY SYSTEM Russian patent published in 2020 - IPC F02C9/30 F04C14/08 F04D15/00 

FIELD: machine building.

SUBSTANCE: invention relates to fuel feed systems and can be used for fuel supply of aircraft gas turbine engines. System comprises fuel pump with electric drive, computer module, pump rpm controller, high-level control system, fuel temperature sensor and a measuring device with a constant flow area, equipped with a differential pressure sensor on the measuring device. Electric drive includes motor and control unit of its rotation frequency. Fuel temperature sensor is installed at the pump outlet, the first input of the computing module is connected to the higher-level control system, which generates the required value of mass flow rate of fuel, computation module second input is connected to fuel temperature sensor output, first pump speed controller first input is connected to computer module output, and controller output is connected to input of electric motor rpm control unit. Measuring device is installed behind the fuel temperature sensor, the pump outlet is interconnected with the measuring device input, the pressure difference sensor output on the measuring device is connected to the pump rpm controller second input, and the computing module is configured to determine the required differential pressure value on the measuring device.

EFFECT: technical result is higher accuracy of determining fuel consumption when fed into GTE.

1 cl, 1 dwg