AIRCRAFT TURBINE ENGINE WITH EPICYCLIC REDUCTION GEAR HAVING A VARIABLE REDUCTION RATIO

The invention relates to an aircraft turbine engine, including at least one rotary body comprising a compressor rotor and a turbine rotor connected to one another by a rotor shaft, the turbine enginebeing configured to drive a member by said shaft via an epicyclic reduction gear (32), said reduction...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	FULLERINGER BENJAMIN, CAZAUX YANNICK, LECOUVREUR DAMIEN
Format:	Patent
Sprache:	chi ; eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GEARING GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING THERMAL INSULATION IN GENERAL WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!