METHOD OF OPERATING AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2012 - IPC F02C7/06 

FIELD: engines and pumps.

SUBSTANCE: proposed engine comprises turbocompressor unit, combustion chamber, jet nozzle, ACS, air feed system, engine cooling system equipped with fuel and hydraulic oil systems with appropriate pumps. Pumps include one delivery pump and set of discharge pumps, suction and pressure oil lines. At least, one of said pumps represents gerotor pump with driven shaft, at least one pair of offset gears and shaft axial retainers made up of cylindrical pin and stopper in congruent contact like ledge-recess. Bellow loop air release device is arranged in oil delivery line and represents jet nozzle located in air section of one of oil cavities at its whatever lubing point to be communicated with bellow loop via oil line. In starting the engine, combustion chamber is initiated to force oil in the system by force pump. Oil is fed from oil tank to force pump inlet and, further, into bellow loop wherefrom it is fed into oil cavities in two paths: via one branch of oil delivery line to oil cavity injectors and, via another branch, to air release device.

EFFECT: improved operation of oil system, higher reliability and longer life of engine components, reduced oil losses.

5 cl, 4 dwg