FIELD: double-flow turbojet engines. SUBSTANCE: device has turning doors integrated in external wall of secondary gas flow annular channel during its operation under direct thrust whose motion is controlled by lift to interfere with deflection of gas flow being reversed. Two primary locks rigidly coupled with fixed structure of device first along flow arranged on either side of central line of door are in mechanical contact with this door at a time in flying configuration of mentioned device and mentioned door is held without spatial misalignment or projection relative to external and internal rims of engine nacelle. EFFECT: improved implementation of desired aerodynamic characteristics. 7 cl, 8 dwg
