FIELD: engines and pumps.
SUBSTANCE: gas turbine engine is designed to maintain the temperature at high-pressure compressor outlet in the range from 621 to 732°C at take-off, and the outflow speeds ratio is determined as the ratio of fan jet outflow speed to the main jet outflow speed and is in the range from 0.75 to 0.90 in flight at cruise engine power at the altitude of about 10668 meters (35,000 feet) at a speed of about 0.80 Mach number. Engine bypass ratio exceeds 8.0.
EFFECT: increased engine efficiency and reduction of fuel consumption.
28 cl, 2 dwg
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