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High-tip-speed fiber composite compressor blades: Vibration and strength analysisAn analytical procedure is described which couples composite mechanics computer codes with NASTRAN. This procedure was used to perform a detailed analysis of a high-tip-speed fiber composite compressor fan blade. The results indicate that the various vibration modes of this blade are highly coupled. Mechanical load ply stresses are well below the corresponding room temperature strengths. Lamination residual stresses are likely to cause transply cracks and interply delamination. Transply cracks and relaxation of root fixity decrease the vibrational frequencies whereas centrifugal stiffening increases them. Comparisons of results for various parameters are presented in tabular and graphical form.
Document ID
19740022220
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chamis, C. C. (NASA Lewis Research Center Cleveland, OH, United States)
Lynch, J. E. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 24, 1974
Subject Category
Structural Mechanics
Report/Patent Number
E-8042
NASA-TM-X-71589
Report Number: E-8042
Report Number: NASA-TM-X-71589
Meeting Information
Meeting: Conf. on Fibrous Composites in Flight Vehicle Design
Location: Dayton, OH
Country: United States
Start Date: May 22, 1974
End Date: May 24, 1974
Sponsors: AFFDL, AFML
Accession Number
74N30333
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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