FIELD: aviation.
SUBSTANCE: invention relates to aircraft engineering, in particular to methods of controlling a gas turbine engine. In a known method of controlling a gas turbine engine, comprising varying the flow rate of cooling air supplied to the turbine depending on the engine operating modes, air is supplied from a power source to the cooling air manifold, linked through an air duct with the control unit and with the cooled turbine path through throttling sections of the overlapping devices made in the form of on-off valves uniformly arranged on the circumference of the engine, adjustment of air supply to the valves from the control unit through a command manifold to open/close them, according to the proposal, the valves are divided into at least two groups, each of which is connected by the command manifold to the control unit, wherein the opening/closing control of each of the valve groups is performed separately or together, depending on the engine operating modes. Power source used is a secondary combustion air zone or the zone at the outlet of a heat exchanger. Expected technical result is a decrease in the specific fuel consumption of the engine due to a decrease in the air flow entering the cooled turbine path on the throttling modes while maintaining the required temperature state of the turbine elements.
EFFECT: if strength standards are observed, the proposed group shutdown of the air going to cool the turbine, engine efficiency significantly improves for the longest operating modes of the typical flight cycle of the engine.
1 cl, 3 dwg
