| 摘要 |
PROBLEM TO BE SOLVED: To provide an aircraft gas turbine engine with multiple fan bypasses. SOLUTION: A first bypass inlet 42 to a fan bypass duct 40 is arranged between first and second fans 31, 33 in their axial directions, and a second bypass inlet 46 is arranged between the second fan 33 and an annular core engine inlet 47 in their axial directions. A fan shroud 108 divides a second stage fan blade 36 into an inside fan hub 37 in the radial direction and an outside front end section 39 in the radial direction. The front end section 39 is arranged in a fan front end duct 146 in the radial direction. An axial translational deflector 44 is positioned so that the deflector closes the fan front end duct 146 when opening the first bypass inlet 42 and it opens the fan front end duct 146 when closing the bypass inlet 42. COPYRIGHT: (C)2005,JPO&NCIPI
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