Experimental Stress Analysis of the TF-30 Turbine Engine Third-Stage Fan-Blade/Disk Dovetail Region.
Abstract
Two-dimensional photoelastic and holographic analysis of the disk/blade dovetail region of the third stage of the TF-30 turbine engines shows a stress concentration factor of 5.2 in the disk fillet and 4.8 in the blade fillet relative to the average stress in the neck section of the disk. Stress distributions along the edges of the fillets and on several interior lines in the disk lug are also reported. Preliminary redesign of the disk fillet indicates that a 27% reduction in the fillet stress of existing third-stage disks is possible by remachining the relief area between the blade and disk lugs.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 26, 1977
- Accession Number
- ADA955333
Entities
People
- R. J. Sanford
- V. J. Parks
Organizations
- United States Naval Research Laboratory