Nacelle for turbomachine

Abstract

The invention relates to a propulsion assembly (1) for an aircraft extending along a longitudinal axis (X) comprising a turbomachine (2), a pylon (3) which connects the turbomachine (2) to the wing of the aircraft, an internal fairing (4) which surrounds the turbomachine (2), an external fairing (5) which circumferentially surrounds the internal fairing (4) and which includes a first cowling (10A) and a second cowling (10B) which are capable of passing between a closed position and an open position, and a casing (7) which circumferentially surrounds said turbomachine and which is located immediately upstream of said external fairing (5). Each of said covers (10A, 10B) comprises a proximal portion (20A, 20B) and a distal portion (30A, 30B) which circumferentially extends said proximal portion (20A, 20B) in said closed position, said proximal portions (20A, 20B) being fixed relative to each other and to said housing (7). Figure 2