GAS TURBINE ENGINE OPERATING METHOD AND GAS TURBINE ENGINE Russian patent published in 2020 - IPC F02C7/10 

FIELD: machine building.

SUBSTANCE: method of gas turbine engine operation, in which air, at least from one compressor, enters the first combustion chamber acting behind the compressor unit, the first turbine acting behind the first combustion chamber, the second combustion chamber acting behind the first turbine, and a second turbine, acting after the second combustion chamber, which is self-igniting, wherein in the compressor stages a cycle is realized, in which atmospheric air is compressed by the multistage cooled downstream compressor to a predetermined pressure, then at the outlet of the last stage of the compressor the air is heated, without mixing in the heat exchanger, with exhaust gases supplied from the turbine, then it is reheated in the combustion chamber, into which fuel is supplied and then through the fixed nozzle device, which forms the specified field of working gas flow rates and is directed to the turbine stage inlet, in which starting from the first and including the penultimate service, before each stage, fuel is supplied through radially directed to the turbine shaft and the units of nozzles fixed on the turbine housing and is uniformly sprayed on the flow section of the turbine in an amount which provides heating of the working gases to a predetermined temperature, said working gas rotating at an angular speed of rotation of the turbine shaft, then successively enters into each stage through rigidly installed on the shaft of the turbine cellular nozzle units, in which, due to geometrical effect, increased component of gas velocity in axial direction relative to turbine shaft and further along working nozzle outlet working gas flows over turbine blade aerodynamic profiles installed on shaft in radial direction, which rotate together with nozzle device and which transmit to said shaft mechanical energy in amount, equal to heat energy received from fuel combustion at the beginning of this stage, which provides rotation of turbine with equal amount of used mechanical energy and added heat energy in stages from fuel combustion in flow of working gas of nozzles supplied by units, installed before entrance to stage, and which maintain preset operating parameters with isothermality coefficient of not less than 0.95, and then working gas enters the last stage, in which without performing heating in the beginning of the stage, final expansion of working gas and lower temperature at the outlet, and then the working gas is directed to the heat exchanger, in which heat exchange is performed between it and the compressed air flow in the compressor, and as specified above, is directed to the heating chamber, and the said working gas is directed further into the atmosphere by closing the cycle.

EFFECT: creation of such a gas-turbine engine, in which a process with a thermodynamic cycle is realized, which differs by efficiency from the Carnot isothermal cycle by less than 10 %, which enables to achieve high efficiency close to the Carnot cycle.

14 cl, 8 dwg