Experimental Stress Analysis of the TF-30 Turbine Engine Third-Stage Fan-Blade/Disk Dovetail Region.
NAVAL RESEARCH LAB WASHINGTON DC
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Two-dimensional photoelastic and holographic analysis of the diskblade 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.
- Jet and Gas Turbine Engines