FIELD: double-flow turbojet engines. SUBSTANCE: reverser of first design version has turning doors integrated into outer wall of secondary-air passage during forward thrust operation and prevent deflection of this gas flow during thrust reversal. Mentioned door turns about its axis in its rear part along flow path. Front side of this turning door enters mentioned secondary-air passage and entire door remains inside external outlines of engine nacelle. Turning door has inner space that forms nozzle between first opening along flow path on front end, internal panel, external panel, and second opening made between rear edge of flap along flow path and mentioned external panel. During thrust reversal, at least some portion of deflected gas flow is passed through mentioned space of bucket-shaped turning door. During forward thrust mentioned second opening is closed by lip joined to fixed structure of reverser so that forces acting on internal panel at gas flow side keep the door closed. Reverser of second design version has at least one door turning by means of lever hinged to its fixed structure and turns about axis in rear part along flow path; it is fixed to rear structure which is free to perform translational motion along flow path. EFFECT: improved safety, reduced mass, and improved aerodynamic characteristics of thrust reverser. 19 cl, 38 dwg
