METHOD OF GAS TURBINE ENGINE COOLING (VERSIONS), METHOD OF CONTROLLING GAS TURBINE ENGINE, GAS TURBINE ENGINE AND ITS ROTOR Russian patent published in 2013 - IPC F02C7/12 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine is cooled to feed fuel to its bladed rotor to cool rotor and its blades by fed fuel. Note here that, at least, one blade with fuel flowing there through is stopped relative to engine combustion chamber so that all fuel flows in combustion chamber at point located radially inside relative to, at least, one blade. Fuel is discharged from rotor directly into combustion chamber. In compliance with another version, fluid is passed along, at least, one first flow path from engine rotor first side to its second side. Fluid thermosiphon flow is created at, at least, one second fuel flow path. Note here that, at least, one second flow path is communicated wit, at least, one second path and is thermally related with, at least, one blade coupled with rotor or its section. At least, one flow path allows fluid flowing hereby without necessity in flowing of said fluid along, at least, one second flow path. Note here that, at least, one second flow path comprises set of second paths in, at least, one blade. Said set of second flow paths allows intercommunication of said flows nearby second end of second flow paths located nearby, at least, one blade point and remote from first flow communicated with, at least, one first flow path.

EFFECT: better heat exchange, higher engine efficiency.

32 cl, 6 dwg