Interactive Multimode Blade Impact Analysis

[+] Author and Article Information
A. Alexander

Hercules Incorporated, Allegany Ballistics Laboratory, Cumberland, Md.

J. Eng. Power 104(2), 286-295 (Apr 01, 1982) (10 pages) doi:10.1115/1.3227278 History: Received December 11, 1980; Online September 28, 2009


This paper describes the theoretical methodology used in developing an analysis for the response of turbine engine fan blades subjected to soft body (bird) impacts and the computer program that was developed using this methodology as its basis. This computer program is an outgrowth of two programs that were previously developed for the purpose of studying problems of a similar nature (a three-mode beam impact analysis and a multimode beam impact analysis). The present program utilizes an improved missile model that is interactively coupled with blade motion which is more consistent with actual observations. It takes into account local deformation at the impact area, blade camber effects, and the spreading of the impacted missile mass on the blade surface. In addition, it accommodates plate-type mode shapes. The analysis capability in this computer program represents a significant improvement in the development of the methodology for evaluating potential fan blade materials and designs with regard to foreign object impact resistance.

Copyright © 1982 by ASME
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