Modeling of Composite Turbo-Propellers Using an Efficient Six-Node Triangular Finite Element

摘要

A recently developed triangular plate/shell finite elmeent is used to model the behavior of spinning advanced composite turbo-props. The element has the capabilities to model very thick to very thin laminated composite structures accurately. The variable thickness modeling capabilities of the element are verified by comparison with results available in literature. Results are presented both for an isotropic (titanium) turbo-propeller blade and for a blade with similar geometry made with advanced composite materials (graphite/epoxy). these results are compared with experimental results available from tests carried at NASA Lewis Research Center. The finite element model is shown to be a reliable simualtion of the actual structure which can be used for refinement of the design without the high cost of actual manufacture and testing.