The parametered modeling technology study for the civil aircraft engine fan blade

Abstract

Purpose

The purpose of this paper is to introduce parametered modeling technology for the civil aircraft engine fan blade, to design the fan blade rapidly and accurately.

Design/methodology/approach

The entire fan blade consists of three crucial parts: blade airfoil, tenon and airfoil root. Blade airfoil with a free surface feature is formed through the blade profiles from the hub to tip in the radial direction. The non‐uniform rational basis spline (NURBS) is utilized to describe the blade profile. The geometry model of fan blade tenon is generated by extruding the sketch of the tenon. And the fillet section is designed to achieve the smooth transition of the up surface and the bottom surface of the blade root. Furthermore, the fan blade of a typical commercial engine is redesigned by the above method.

Findings

The stress analysis of the fan blade shows that the fan blade model designed in this work is reasonable.

Originality/value

The parametered fan blade model is presented on the basics of feature‐based modeling technology.

Citation

Zeng, H. and Sun, Y. (2012), "The parametered modeling technology study for the civil aircraft engine fan blade", Multidiscipline Modeling in Materials and Structures, Vol. 8 No. 1, pp. 96-104. https://doi.org/10.1108/15736101211235994