| 摘要 |
A gas turbine engine for an aircraft capable of cruise operation at altitudes in excess of 30,000 feet and at mach numbers in excess of 0.6, comprises a core engine including a compressor 12 which is effective for producing a maximum pressure ratio in excess of 40:1. The engine further comprises a propulsor 20 having an air bypass ratio between 10:1 and 60:1. The engine further comprises means for varying the pressure ratio so that the increase in pressure ratio from take-off to cruise is in excess of 20%. <IMAGE> |
