| 摘要 |
PROBLEM TO BE SOLVED: To provide a supersonic type aircraft turbofan engine improved in variable cycle performance, efficiency, and noise damping performance. SOLUTION: The turbofan engine 10 includes first and second fans 14, 16 each independently connected to turbines 26, 24. A first bypass pipe passage 46 is arranged to surround a core engine and communicate with the second fan 16. A second bypass pipe passage 48 surrounds the first bypass pipe passage 46 and is communicated with the first fan 14. A first discharge nozzle 66 is connected to both the core engine and the first bypass pipe passage 46. Further, a second discharge nozzle 68 is connected to the second bypass pipe passage 48. COPYRIGHT: (C)2007,JPO&INPIT |
