The theoretical methodology used in developing an analysis for the response of turbine engine fan blades subjected to soft-body (bird) impacts is reported, and the computer program developed using this methodology as its basis is described. This computer program is an outgrowth of two programs that were previously developed for the purpose of studying problems of a similar nature (a 3-mode beam impact analysis and a multi-mode 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.

  • Corporate Authors:

    Hamilton Standard

    Windsor Locks, CT  United States  06096
  • Authors:
    • Alexander, A
    • Cornell, R W
  • Publication Date: 1978-8

Media Info

  • Pagination: 301 p.

Subject/Index Terms

Filing Info

  • Accession Number: 00192303
  • Record Type: Publication
  • Source Agency: National Technical Information Service
  • Report/Paper Numbers: NASA-CR-159462 Final Rpt.
  • Contract Numbers: NAS3-20091
  • Files: TRIS
  • Created Date: Jul 31 1979 12:00AM