FIELD: engines and pumps.
SUBSTANCE: control method of air leakages and flow for turbine cooling in double-flow gas turbine engine involves determination of air flow Gac at compressor inlet, air flow Gat through nozzle device of turbine and air flow Gal for leakages and for cooling of turbine; at that, air flow Gal through nozzle device of turbine is determined by mathematical processing of flow values of fuel, air temperature and pressure before and after compressor, rotor rpm of compressor, which are measured during engine test; air flow Gac at compressor inlet is determined as per compressor characteristic connecting air flow, rotation speed and pressure increasing degree, taking into account pressure increasing degree of compressor and reduced compressor rpm calculated as per parametres measured during engine test, and air flow Gac for leakages and cooling of turbine is determined by difference between air flow Gac at compressor inlet and air flow Gat through nozzle device of turbine.
EFFECT: invention allows improving accurate control of leakages and flow of air taken for cooling of turbine in double-flow gas turbine engine.
1 dwg
