Research On Design And Manufacture For Composites Blade In Aircraft Turbin

The usage of composites blade is one of the most important measures for weight saving which holds significance value to realise large thrust-weight ratio and high fuel efficiency of aircraft turbins. In order to achieve the industrial application level of the composites blade, this paper carries out the related researches on lay-up design, placeability analysis and manufacture of the blade.The paper studies the lay-up design by finite element method and establishes the mechanical model in accordance with geometrical model and service condition of the blade. Then the paper forecasts the properties of the composite material by mesoscopic mechanics and screens out the suitable material which satisfies the demand of strength and stiffness, the selected matial is T800/ epoxy resin.Then the paper calculates the thickness of different regions based on the properties of the selected material and the geometrical model, Furthermore, the paper designs the lay-up sequence of the composites blade refers to the criteria of the composite material. The sequence of the blade is [±45/08/±45]s, the hub as well as the joint is [±45/903/04/903/04/903/04/±45]s.According to the provided geometrical model and character of deformation of the blade, the paper promotes the placeability technology of complex surface and raises an analytical method about complex surface of composites component based on fiber deformation constraints and ply-orientation constraints. The method can not only meet the demand of the fiber placement process, but also guarantee the mechanical properties. The algorithm is programmed through Visual Basic 6.0 compile software module based on CATIA automation technology and verified by the hyperboloid model and the blade model.The mould is designed for the composites blade, also the manufacture technology is studied. Firstly, the paper chooses the material USN 12500 carbon fiber/ epoxy resin as experimental material and tests the tensile properties, compression performance, interlaminar shear strength and the mode I interlaminar fracture toughness property. Then the resin absorption is studied by testing the glue uptake and the degree of cure. Furthermore, the paper explores the relation between resin absorption and internal defects. At last, the composites blade is solidified though mould pressing technology to obtain the strong interlayer bonding.