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) is rotated by a third shaft (9) of a turbine, and the first shaft (10) is guided in rotation with respe...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	BRAULT MICHEL GILBERT ROLAND, MORREALE SERGE RENE, VERDIER MARION JEANNE PIERRETTE, BENSLAMA YANIS, CUVILLIER ROMAIN GUILLAUME
Format:	Patent
Sprache:	chi ; eng
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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