Deformation Design Of Pre-deformation Design Fan Blade Structure

Traditional design methods of aircraft engine fan blades, although there are many advantages, but are unavoidable according to the work environment to design blades. In the course of their work, will have the joint action of the airfoil in aerodynamics and centrifugal deformation, resulting airfoil deviations occur,inconsistent with the original design of the airfoil, so leaves pre-deformation design analysis to ensure that the fan blades in practice consistent run size and design of the original size or reaching agreement.In recent years, composite materials in the aviation engine is a new research direction. Composite materials because of its large specific strength, high stiffness,good fatigue performance, can be designed in excellent condition laid in the way content and internal structure of the inside of the fiber and the like, gradually replaced the original metal-based material, and become an important aviation engine fan blades one of the materials, so composites fan blades pre-deformation design has important practical significance.(1) the use of UG / Open API functions and Menuscript modules rely on the support C / C ++ programming language, the compiler in VS2010, completed a composite fan blades parametric modeling. And then leaves the body as a whole to create all run automatically by the program code to achieve the three-dimensional parametric modeling from point to a line and then to the surface, lay the foundation for the subsequent finite element analysis of the key points from the imported base to build blade section line.(2) based on the work and mechanical performance requirements of the blade,anisotropic composite materials(HT3 / 5224) as the fan blade material, using ANSYS software to complete the setting blade elasticity coefficient related projects, the application SOLID46 unit blade model establishment of laminate structure, and finally loading the aerodynamic and centrifugal forces to blade model, complete deformation analysis.(3) Using APDL language, the difference between the original leaf extract displacement and deformation of the airfoil between after using reverse superposition iterative calculation nodes displacement between the maximum displacementdifference between the original model and the design model superimposed after the displacement after the first iteration of 0.1994 mm, after 15 iterations, the maximum displacement of magnitude difference has dropped to 10-8(mm) units, the results showed that at the time of 10-6(mm) units for space node coordinate has been reached for the convergence conditions, indicating pre-deformation model has been to meet the design requirements.In summary, the paper completed the parametric modeling of composite fan blades, set the related composites engineering modulus of elasticity, pneumatic centrifugal load interpolation, iteration displacement difference and a pre-distortion design airfoils. On composite fan blade design has a certain reference value.