RU1793083C - Fuel system for gas-turbine engine - Google Patents

Description

P bozduha

The invention relates to engine building. predominantly aviation, and can be used in sectors of the national economy, in which low and high pressure units are used to supply fuel to the combustion chambers.

The aim of the invention is to reduce labor costs for the maintenance of a gas turbine engine and increase its reliability.

The drawing shows a schematic diagram of the fuel system of a gas turbine engine.

It consists of a fuel tank 1, which is under overpressure, a flowmeter 2. a fire valve 3, a motor centrifugal pump 4, a filter 5, units of the main 8 and afterburner 11 circuits, each of which includes a high pressure pump, a fuel regulator having a drain fuel cavities in communication with the inlet of the high pressure pump, fuel main 9 and afterburner collectors, high 12 and low 7 pressure discharge pipelines, check valve 6 and nozzles 13.

In the process of engine operation, fuel from tank 1, flow meter 2, fire valve 3 passes through an additional centrifugal pump 4 and fuel filter 5. From filter 5, fuel enters the units of the main 8 and afterburner 11 circuits and then to the fuel main 9 and afterburner 10 collectors. Part of the fuel from the high-pressure cavities of units 8 and 11 through pipelines 12 enters the inlet of the motor centrifugal pump 4. B

drain pipelines 12 due to a significant pressure drop, the equilibrium state of the air dissolved in the fuel is disturbed, part of which, having separated in the free state, enters the fuel filter 5 and units 8 and 11. Free air entering the units will be collected in its upper part , where did the jets 13 go, through the drain pipelines 7 and the non-return valve b will go to the fuel tank 1. The non-return valve 6 prevents the fuel from entering the internal cavities of the units of the main and afterburning circuits from the tank e plane. Permanent bleeding of fuel from the internal cavities of the units will allow to remove the air that has got into the internal cavities of the units during their installation, and will also exclude the possibility of its accumulation in the units during operation of the engine.

Thus, the connection of the upper sections of the drain cavities of the units of the main and afterburner circuits, which are a place of accumulation of free air, with 5 fuel tanks, pipelines with jets and a non-return valve, will make it possible to cancel the operation in operation - pumping the fuel system of a gas turbine engine and to prevent accumulation of free air in internal cavity x units during operation of the engine.

Using the proposed technical solution will reduce labor costs for engine maintenance and increase its reliability.

0

5

0

0

5

Claims (1)

SUMMARY OF THE INVENTION A gas turbine engine fuel system comprising a pressurized fuel tank, primary and afterburner assemblies, each of which includes a filter, a high pressure pump, a fuel regulator having drain fuel cavities in communication with a high pressure pump inlet pressure and fuel lines, characterized in that, in order to increase reliability and reduce maintenance work costs, it is equipped with an additional line with a non-return valve and pipelines with nozzles connecting the upper portions of the drain fuel cavities with an additional line, the latter being in communication with the fuel tank. ..