AXIAL COMPRESSOR BLADE MAKING METHOD

摘要

aircraft industry; turbofan engines. SUBSTANCE: according to proposed method, two flat blanks of variable-thickness aerofoil portions are connected by diffusion soldering over links and soldered pair is twisted to form required profile after which it is subjected to finishing machining. Two longitudinal cavities and longitudinal link are formed on flat inner sides of blanks. Blank of blade pressure surface is made with chord less than chord of blade and provided with sharpened wedge-like edges. Corresponding wedge-like slots are made in blank of blade back. Blanks are connected so that sharpened edges of pressure surface get into wedge-like slots of blade back. For this purpose, pressure surface blank is deformed to increase sag. Then connected blanks are placed in mould into furnace for diffusion soldering. Then blade aerofoil portion profile is formed and is subjected for finishing machining. EFFECT: reduced weight of blade, preserved configuration f profile, provision of strong seams. 2 cl, 2 dwg