FIELD: machine building.
SUBSTANCE: invention relates to gas turbine engines and can be used in axial fans, compressors and turbines of aircraft turbojet engines and ground-based gas-turbine plants in order to protect against penetration at breakage of the blade. Device for localization of broken blade (2) of turbojet engine fan consists of external force impenetrable (3) and internal pierced (4) coaxial fan housings, interconnected by detachable connection to annular cavity (6) between them, located above the fan rotor blades, in annular cavity (6) equidistant to its surfaces at least three layers of hollow metal spheres (7) filled with inert gas.
EFFECT: device allows maximum absorption of kinetic energy of fragment of detached blade and thus eliminates need to reinforce and accordingly weight outer housing to prevent its penetration, as well as simplify design.
1 cl, 2 dwg
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