FIELD: transport.
SUBSTANCE: nacelle 1 comprises air intake 5 arranged ahead of turbojet engine 2, medium section, inner casing 6a to cover engine fan 3 and rear section 7 with outer element 7a. Said outer element 7a is jointed with fan casing rear section 61 to support turbojet engine 2 and incorporates means of joint with engine pylon to be connected with aircraft fixed element 13.
EFFECT: optimised clearance between fan vanes and engine inner vanes and their appropriate cases.
28 cl, 18 dwg
