FIELD: internal combustion engines.
SUBSTANCE: gas turbine engine comprises a fan section comprising a fan section including a fan rotatable about an axis and a speed reduction device. Speed reduction device is in communication with the fan and includes a star drive gear system with a star gear ratio of at least 1.5. Fan is rotatable with a blade tip speed of more than 1150 but less than 1400 feet per second. Bypass ratio ranges from 11.0 to 22.0.
EFFECT: technical result of the present invention is to improve the performance of gas turbine engines, including increasing the thermal, transmission and traction efficiency.
10 cl, 3 dwg
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