The invention relates to an extension of an intermediate casing for an aircraft jet engine, intended to project towards the downstream end from an external shell of the intermediate casing, this extension comprising an annular connecting downstream end forming an annular groove open radially towards the outside, intended to receive nacelle covers. According to the invention, the annular connecting downstream end is produced by means of a plurality of angular sectors.
INTERMEDIATE CASING EXTENSION FOR AN AIRCRAFT JET ENGINE, COMPRISING A SECTORISED ANNULAR GROOVE FOR RECEIVING THE NACELLE COVERS
PROLONGEMENT DE CARTER INTERMEDIAIRE POUR REACTEUR D'AVION, COMPRENANT UNE GORGE CIRCULAIRE SECTORISEE POUR RECEVOIR LES CARENAGES DE LA NACELLE
26.01.2016
Patent
Elektronische Ressource
Englisch
IPC: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64C AEROPLANES , Flugzeuge / 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 |
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