| 摘要 |
A propulsion engine for an aircraft includes a first fan having a set of first blades and a second fan having a set of second blades. There is provided a first angular pitch adjustment mechanism coupled to the first set of blades, a second angular pitch adjustment mechanism coupled to the second set of blades and an actuation means coupled to the first angular pitch adjustment mechanism. The first and second angular pitch adjustment mechanisms, are coupled together such that when the actuation means generates an output, the angular pitch of each of the first blades and each of the second blades changes.
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