GAS TURBINE ENGINE COMPRESSOR FUEL SUPPLY AND MECHANIZATION SYSTEM Russian patent published in 2024 - IPC F02C9/30 F04D27/00 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft gas turbine engine (GTE) fuel feed and control system in stationary and variable modes taking into account external conditions of aircraft flight. In the system, the low-pressure fuel pump and the high-pressure fuel pump are combined into a first integral unit which comprises a low-pressure boost stage and a high-pressure stage. Booster stage outlet is connected via fuel pipeline with engine fuel-oil heat exchanger inlet. Output of the fuel-oil heat exchanger is connected through another fuel pipeline to the input of the fuel filter, the output of which is connected to the input of the high-pressure stage of the first integral pump unit. Device for dosing fuel Gt into the gas turbine engine combustion chamber and the automatic distributor of fuel on the manifolds of the combustion chamber are combined into the second integral unit. High-pressure compressor (HPC) guide vanes position control and air bypass from low-pressure compressor booster stages is carried out by means of power hydraulic cylinders at the command of the second integral unit, compressor mechanization device additionally comprises an electropneumatic unit and at least one pneumatic cylinder connected to it, providing opening/closing of bypass valves and/or air bleeding from GTE HPC, wherein GTE compressor is additionally provided with at least one air bleed point to feed compressed air via air pipelines to electropneumatic unit. To control the second integral unit and the electropneumatic unit, an electronic control unit is additionally introduced, wherein the mechanical drive of both fuel pumps of the first integral unit is carried out by the same drive shaft of the drive unit box. Besides, digital electronic engine controller is used as an electronic control unit. Air bleeding for supply of compressed air through air pipelines to electropneumatic unit is provided from HPC stage. Opening/closing of air bypass valves from HPC is performed according to relay program depending on high pressure rotor_hp0 speed based on the air temperature at HPC inlet. A gear pump is used as a high-pressure stage of the first integral unit.

EFFECT: invention enables to reduce the weight of the system, create an efficient and fireproof system, which provides uninterrupted fuel supply to the combustion chamber in all operating modes of the engine, including starting the engine on the ground and in the air, and also to increase reliability and operational manufacturability of arrangement of drive units on a box of drive units.

5 cl, 1 dwg