An analysis of impact resistance of composite blades for aircraft engines (analysis with two dimensional and three dimensional finite elements)

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An analysis of impact resistance of composite blades for aircraft engines (analysis with two dimensional and three dimensional finite elements)

Miyaehi, T. / Okumura, H. / Ohtake, K.

An analysis has been conducted to determine the feasibility of composite fan blade for meeting impact resistance requirements for aircraft engines. Triangular plate elements were used in previous analysis. The results of the previous analysis agreed well with the experimental results for non-rotating blade. However, for rotating blades, no analysis nor experiment had been conducted. In this analysis, plate elements and three dimensional elements were used for finite element analysis and the effect of centrifugal force was taken into account. Impact response of six fan blade models were calculated. According to the results of the analysis with plate elements, the bending deformations are decreased significantly by centrifugal force. However, torsional deformations and local deformations are not significantly decreased. It seemed to indicate that the effect of centrifugal force on impact resistance of composite fan blade is not appreciable. Beside the analysis with plate elements, an analysis with 3D (8-node brick-type) elements was conducted in order to evaluate out-of-plane stress in the blades. However, the results of vibrational analysis with 3D elements for a long, thin cantilever blade do not agree well with experimental results at present.