| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To provide an aircraft gas turbine engine of a FLADE double counter-rotating fan type. <P>SOLUTION: An embodiment of this engine 1 includes one row of FLADE fan blades 5 disposed radially outwardly of and drivingly connected with one of axially spaced-apart first and second counter-rotating fans 130, 132. A core engine 18 located at an axial downstream part of the first and second double counter-rotating fans is circumscribed by a fan bypass duct 40 formed at the axial downstream part of the first and second double counter-rotating fans. The row of the FLADE fan blades 5 radially extends across a FLADE duct 3 circumscribed about the first and second double counter-rotating fans and the fan bypass duct 40. A second low pressure turbine 21 is drivingly connected with the first double counter-rotating fan 130, and a first low pressure turbine 19 is drivingly connected with the second double counter-rotating fan 132. <P>COPYRIGHT: (C)2005,JPO&NCIPI</p> |
