FIELD: internal combustion engines.
SUBSTANCE: device comprises a pneumatic turbine mechanically connected to said gas turbine engine for its rotation to ensure its reactivation; pneumatic accumulator connected to said pneumatic turbine via pneumatic feed circuit with gas under pressure of said pneumatic turbine; a controlled pneumatic quick-release valve mounted on the pneumatic circuit between said battery and said pneumatic turbine and configured to switch over at least one open position, in which gas can feed said pneumatic turbine, or into closed position, in which said pneumatic turbine ceases to receive power with gas under pressure.
EFFECT: invention relates to fast reactivation of a helicopter gas turbine engine.
12 cl, 6 dwg
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