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 device coupled to the first angular pitch adjustment mechanism. The first and second angular pitch adjustment mechanisms are coupled together such that when the actuation device generates an output, the angular pitch of each of the first blades and each of the second blades changes.
Propulsion engine
2016-09-20
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
Online Contents | 2005
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