AIRCRAFT TURBOMACHINE WITH REDUCTION GEARSET

The invention relates to a turbomachine (1) comprising a single ducted fan (2) including a first shaft (10) rotated by a second shaft (16) via a speed reduction gearset (11), the second shaft (16) being rotated by a third shaft (9) of a turbine, the first shaft (10) being guided in rotation with res...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	VERDIER, Marion, BRAULT, Michel, CUVILLIER, Romain, MORREALE, Serge, BENSLAMA, Yanis
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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