Composite materials in aircraft engine blades

The article investigates the strength of propeller blades made a multilayer composite material, subjected to centrifugal and gas loads with various combinations fiberglass carbon fiber orientation material base. finite element method is used as research method. A blade in turbines jet engines compressors, materials, considered naturally twisted rod, provided that hypothesis flat sections across thickness package valid under conditions rigid contact at boundary layers. propfan model modeled by four-node elements natural curvature forty-eight degrees freedom, taking into account compression normal. applied for calculating makes it possible assess an arbitrarily reinforced layer layer. hydrodynamic first second stages were action loads. stress was determined 17 points 21 cross-sections As result study, parameters different ratios dissimilar materials layers obtained. Conclusions are drawn, based on fact have significant advantages terms weight characteristics compared traditionally technology manufacture propfans.