FIELD: aircraft engine building.
SUBSTANCE: proposed group of inventions relates to aircraft bypass turbojet fan blade length 700÷1,500 mm with dampener for damping vibrations. Disclosed is a long hollow hollow-arm fan blade of aircraft bypass turbojet engine, comprising two halves made of titanium alloy, made integral with lock part and with load-bearing elements, connected to locking part and located on part of blade root length forming blade shell, "dovetail" lock and ribs made at both edges of blade and inside blade body. Central power member—side member or two side members—are also made of titanium alloy in form of rod with length, less than length of blade, with locking part in the form of "dovetail" and a feather with gradually narrowing to thickness of the blade with transverse quadrangular or rectangular cross-section. Between the shell and the side-member or side members on both sides of the spar with the required interference δ in mm along crimps tops multi-layer multi-corrugated packs are arranged, harvested corrugations from one, two or more steel, hardened or cold-worked ground or corrugated tapes. Along the edges of the packs there is one smooth steel calf or cold-worked polished band. All tapes are made from refractory stainless steel.
EFFECT: higher reliability by preventing fatigue damages of working blades.
14 cl, 14 dwg
