ASSEMBLY OF INTERNAL FIXED STRUCTURE OF TURBOJET NACELLE AND THERMAL PROTECTION

摘要

The invention relates to an assembly of a fixed internal structure (5) of a nacelle (3) of a turbojet engine (2) and a thermal protection device, said structure (5) having an internal face, to which is reported the thermal protection, and an outer face, constituting a portion of the internal surface of a cold flow vein, the assembly being characterized in that at least one channel puts in fluid communication the inner face and the outer face of the structure (5).