CONCENTRIC SHAFTS DRIVING ADJACENT FANS FOR AIRCRAFT PROPULSION

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 driv...

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Bibliographische Detailangaben
Hauptverfasser: SUCIU, Gabriel L, CHANDLER, Jesse M
Format: Patent
Sprache:eng ; fre ; ger
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Zusammenfassung: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.