An aircraft engine assembly includes a dual-flow turbine engine, a pylon for mounting the turbine engine, thrust-absorbing rods connecting the turbine engine to the pylon, and an inter-flow compartment housing a lubricant tank. In order to facilitate the filling of the tank, a lubricant supply path is fluidly connected to the tank, this path passing through an inner hollow region of at least one of the two thrust-absorbing rods.
Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine
2023-02-07
Patent
Elektronische Ressource
Englisch
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F01M Schmierung von Kraft- und Arbeitsmaschinen oder Kraftmaschinen allgemein , LUBRICATING OF MACHINES OR ENGINES IN GENERAL |
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