Accession Number : ADA955333
Title : Experimental Stress Analysis of the TF-30 Turbine Engine Third-Stage Fan-Blade/Disk Dovetail Region.
Descriptive Note : Final rept.,
Corporate Author : NAVAL RESEARCH LAB WASHINGTON DC
Personal Author(s) : Parks, V. J. ; Sanford, R. J.
Report Date : 26 AUG 1977
Pagination or Media Count : 33
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.
Descriptors : *TURBOFAN ENGINES, *TURBINE BLADES, ANGLES, BLADES, DISKS, HOLOGRAPHY, LUGS, PHOTOELASTICITY, STRESS ANALYSIS, STRESS CONCENTRATION, STRESSES, THIRD STAGE ENGINES, TWO DIMENSIONAL.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE