NACELLE FOR BYPASS TURBOJET ENGINE Russian patent published in 2012 - IPC B64D29/06 

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to turbojet engine nacelle. Proposed nacelle comprises air intake front section, central section accommodating turbojet engine fan 7, and rear section comprises device to fasten nacelle to engine pylon to be jointed to aircraft fixed element. Rear section comprises structural frame 18 with noise-isolation panel 21 with higher aerodynamic properties. Said noise-isolation panel 21 is secured on said frame 18 by not rigid or flexible fastener so that, with air available to create excess pressure in engine compartment, said panel may be deformed in direction 31, in fact, centrifugal and radial relative to turbojet engine 7.

EFFECT: reduced deformation of engine nacelle.

10 cl, 17 dwg