| 摘要 |
<p>A gas turbine engine (62) includes a geared architecture (48) rotatably coupled to the fan drive shaft (40), and a high pressure compressor (54). The gas turbine engine (62) is configured so that a core temperature at an exit of the high-pressure compressor (54) is approximately in a range of 621 to 732°C at take-off and an Exhaust Velocity Ratio, defined by a ratio of a fan stream exhaust velocity to a primary stream exhaust velocity, is approximately in a range of about 0.75 to about 0.90. A Bypass Ratio of the engine is greater than about 8.0.</p> |
