FIELD: aircraft engine.
SUBSTANCE: invention relates to aircraft engine, to ways to increase the resource of the gas turbine engine by the number of launches due to the design of turbine cooling systems. Before cold scrolling and starting the engine, hot air is supplied to the turbine cooling system from an external auxiliary gas turbine engine or from a ground installation and heated for 3-6 minutes, after which the engine is launched. The parameters of the supplied hot air correspond to the parameters of the air supplied for the cooling of the turbine of this engine. In the process of the engine output to the “small gas” mode, hot air is supplied to the cooling system with a higher temperature. Thermal stability of the oil supplied to the engine oil system is provided by the circulation of oil from oil pumps of the engine.
EFFECT: increasing the engine service life in terms of the number of starts, respectively, low-cycle fatigue by reducing the temperature difference in the turbine blades and disks due to their preheating with hot air with a higher temperature.
1 cl, 3 dwg
