FIELD: transport.
SUBSTANCE: invention relates to aviation, in particular to designs of engine nacelles and reversing arrangements of dual-flow turbojet engines. Aircraft nacelle contains supporting structure (100, 110, 200, 300, 400, 500) provided with thrust reverser having bearing frame (45, 201, 301, 401, 501) made of composite material. The bearing frame has essentially opened cross-section provided with at least one reinforcing member. The bearing frame (45, 201, 301, 401, 501) is manufactured using moulding technique by means of resin infusion, specifically via resin transfer moulding (RTM) technique. The supporting structure (100, 110, 200, 300, 400, 500) includes at least one guiding facility (5, 7), in particular of rail type, for installation of movable hood for thrust reverser and being capable to slide. The supporting structure (100, 110, 200, 300, 400, 500) is linked with part of panel (15) of immovable internal structure (17) of turbojet engine aerodynamic shroud.
EFFECT: possibility to lower bearing frame weight while keeping strength characteristics as compared to closed structures made of composite materials.
20 cl, 10 dwg
