FIELD: power industry.
SUBSTANCE: gas turbine based on an aircraft engine contains an air intake chamber, a compressor comprising an air intake device communicating with the noted chamber, a combustion chamber, a high pressure turbine and a power turbine. The forced air flow generator communicates with the air intake chamber. In the channel for air entering the combustion zone, an overlapping device is disposed and is adjusted to provide the noted channel closure and injecting pressure in the noted air intake chamber with a forced air flow generator to a value sufficient for forced pressurized air flow through the noted turbine.
EFFECT: invention improves the gas turbine restarting efficiency.
24 cl, 7 dwg
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