DOUBLE FLOW TURBOMACHINE FOR AIRCRAFT, COMPRISING STRUCTURAL MEANS FOR RIGIDIFYING THE CENTRAL CARTER

摘要

The invention relates to an aircraft turbomachine comprising envelope means (36) arranged in the rear extension of an inner shell (22) of intermediate casing and arranged around a central casing (18). According to the invention, the means (36) comprise on the one hand a structural upstream sleeve (54) mounted on the inner ferrule (22) and defining the front portion (37a) of an inner delimiting surface (37) of the secondary vein, and secondly a main envelope (56) extending rearward upstream ferrule (54). In addition, the turbomachine comprises structural means (72) for stiffening the central casing, surrounded by the casing (56) and extending rearwardly between the upstream shell (22) and the central casing on which these means ( 72) are mounted.