Propulsion engine

A propulsion engine 20 for an aircraft comprises a first fan 30 having a set of first blades 32 and a second fan 40 having a set of second blades 42. There is provided a first angular pitch adjustment mechanism 50 coupled to the first set of blades 32, a second angular pitch adjustment mechanism 60 coupled to the second set of blades 42 and an actuation means 70 coupled to the first angular pitch adjustment mechanism 50. The first and second angular pitch adjustment mechanisms 50, 60 are coupled together such that when the actuation means generates an output, the angular pitch of each of the first blades 32 and each of the second blades 42 changes.