FIELD: engines and pumps.
SUBSTANCE: gas turbine engine (10) of airborne vehicle, namely helicopter, includes gas generator (12) and free turbine (14) rotated with gas flow (F) generated with gas generator. Gas turbine engine includes motor generator (30) electrically connected to accumulator (32) and mechanically connected to shaft (18) of gas generator (12). Accumulator has the possibility, on one hand, of feeding motor generator (30) during acceleration phase of gas turbine engine in order to supply to shaft (18) additional amount of kinetic rotation energy, and on the other hand, for storage in the form of electric energy the amount of kinetic energy taken with motor generator (30) from shaft of gas generator during braking phase of gas turbine engine. Accumulator (32) is made so that it can be recharged with the first electric generator (34) connected to shaft (16) of free turbine (14).
EFFECT: achieving the acceleration degree exceeding the acceleration of gas turbine engine from known level of equipment at the same stall margin, or providing the possibility of development of gas turbine engines with decreased stall margins, which is expressed in preferable reduction of overall dimension of gas turbine engine.
4 cl, 3 dwg
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