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

An aircraft turbine engine includes a rotating body comprising a compressor rotor and a turbine rotor interconnected by a rotor shaft, the turbine engine being configured to drive a member by said rotor shaft via an epicyclic reduction gear, said epicyclic reduction gear comprising a first element (...

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Bibliographische Detailangaben

Hauptverfasser:	Cazaux, Yannick, Lecouvreur, Damien, Fulleringer, Benjamin
Format:	Patent
Sprache:	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
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