Disk Residual Life Studies. Part 2. TF30 10th-Stage Compressor Disk (INCOLOY 901).
Final rept. 1 Apr 76-30 Jun 79,
PRATT AND WHITNEY AIRCRAFT GROUP WEST PALM BEACH FL GOVERNMENT PRODUCTS DIV
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A residual fatigue life prediction method, suitable for Retirement-for-Cause application, has been developed for two PWA turbine disks the F100 1st-stage high pressure turbine disk and the TF30 10th-stage compressor disk. The method is based upon interaction of fracture mechanics crack propagation modeling concepts with laboratory nondestructive evaluation NDE techniques. Fracture mechanics life models were developed using the GPD hyperbolic sine SINH model refined during an earlier Air Force Materials Laboratory AFML program. Stress intensity K solutions for the engine components were based upon experimental effective K determinations made during full-scale component fatigue tests. The NDE techniques developed for disk inspections included acoustic emission AE, eddy current EC, and fluorescent penetrants FP. Stress-enhanced penetrant and semi-automated rotating probe EC techniques were developed as periodic inspections, while the AE time-domain technique was developed as a real-time inspection tool. Author
- Test Facilities, Equipment and Methods
- Jet and Gas Turbine Engines