| 摘要 |
An aircraft gas turbine engine (10) includes high and low pressure turbines (24, 26) having respective counter rotatable low pressure inner and outer rotors (200,202) with low pressure inner and outer shafts (130,140) in part rotatably dispose d co-axially within a high pressure rotor (33) and drivingly connected to first and secon d fan blade rows (13, 15) and first and second boosters (16, 17) respectively. A bypass duct (21) radially bounded by a fan casing (11) and an annular radially inner bypass duct wall (9) surrounds the boosters (16, 17) axially located between the first and second fan blade rows (13, 15). The engine (10) has a high pressure compressor (18) operable to produce an overall pressure ratio in a range of about 40-65 and a fan inlet hub to t ip radius ratio (RH/RT) in a range between .20 and .35, a bypass ratio in a range of 5-15, a n operational fan pressure ratio in a range of 1.4 - 2.5, and a sum of operational fan tip speeds in a range of 1000 to 2500 feet per second.
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