A propulsion system for an aircraft has at least two fans (22, 24; 122, 124; 208, 210), each fan (22...210) having a fan drive shaft (56; 156). A turboshaft gas turbine engine (26, 28; 126, 128; 202, 204) drives each of the at least two fans (22...210), and drive an output shaft (36; 136) which drives a gear (38; 138) to, in turn, engage for driving a gear (40; 140) on a first intermediate shaft (41, 42; 141; 206, 207) extending from the turboshaft gas turbine engine (26...204) in a rearward direction toward an intermediate fan drive shaft (50; 150). The intermediate fan drive shaft (50; 150) drives the fan drive shaft (56; 156), and the first intermediate shafts (41...207) extend over a distance that is greater in an axial dimension defined between the turboshaft gas turbine engine (26...204) and the fan (22...210) than in a width dimension defined between the at least two fans (22...210). The first intermediate shafts (41...207) are concentric.
CONCENTRIC SHAFTS DRIVING ADJACENT FANS FOR AIRCRAFT PROPULSION
BENACHBARTE VENTILATOREN ANTREIBENDE KONZENTRISCHE WELLEN FÜR FLUGZEUGANTRIEB
ARBRES CONCENTRIQUES ENTRAÎNANT DES SOUFFLANTES ADJACENTES POUR LA PROPULSION DUN AÉRONEF
2018-06-13
Patent
Electronic Resource
English
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
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