FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft assembly with engine moving nacelle. Said aircraft assembly 1 comprises turbojet 2, nacelle 4 with nacelle 3. Nacelle comprises moving section 40 that doubles as integral jacket around turbojet section. Note here that said section 40 has circular wall 50 making internal boundary of annular secondary flow channel 24 and circular wall 46 making external boundary of annular secondary flow channel 24. Walls 50 and 46 are furnished with soundproof lining 80. Nacelle moving section slides unobstructed on pylon. Note that rear end 18 of turbojet blower housing 12 with attachments 6a, 6b, 8 locked to attach engine to pylon makes inner radial support for nacelle moving section 40.
EFFECT: decreased wear of turbojet.
8 cl, 6 dwg
