FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, namely, to turbojet aircraft nacelle. Nacelle 1 comprises air intake section 4 to direct airflow to turbojet fan that has lengthwise outer panel 40 integrated with inlet edge 4a. Besides, nacelle comprises central section 5 arranged around turbojet fan. Air intake section 4 is attached to central section to ensure aerodynamic integrity. Also, nacelle has inner panel 41 with sound-absorbing shell 53. Inner panel downstream end is attached to upstream end of central section 5. Besides nacelle incorporates guides 15 to guide outer panel or panels 40 to allow its/their reciprocation relative to nacelle upstream end. Note here that said guides 15 are arranged solely at central section 5.
EFFECT: simplified servicing, better noise absorption.
17 cl, 15 dwg
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