NASA’s turbine seal facility tests air-to-air seals for advanced jet engines. High temperature, speed, and pressure combinations limit test disk life, due to crack initiation in the Grainex Mar-M 247 disk bolt holes. An inspection interval is determined to ensure safe operation. Fatigue strain-life data is presented for test specimens from a test disk. Strain-life models (Manson-Hirschberg method of universal slopes, Halford-Nachtigall mean stress method, and modified Morrow method) were compared to experiment. Using experimental data at −99.95% prediction levels, accounting for six bolt holes at 0.5% total strain and 649°C, the test disk should be inspected after 665 cycles.
Strain-Life Assessment of Grainex Mar-M 247 for NASA’s Turbine Seal Test Facility
Contributed by the International Gas Turbine Institute (IGTI) of THE AMERICAN SOCIETY OF MECHANICAL ENGINEERS for publication in the ASME JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Paper presented at the International Gas Turbine and Aeroengine Congress and Exhibition, Vienna, Austria, June 13–17, 2004, Paper No. 2004-GT-53939. Manuscript received by IGTI, October 1, 2003; final revision, March 1, 2004. IGTI Review Chair: A. J. Strazisar.
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Delgado, I. R., Halford , G. R., Steinetz, B. M., and Rimnac, C. M. (June 24, 2005). "Strain-Life Assessment of Grainex Mar-M 247 for NASA’s Turbine Seal Test Facility ." ASME. J. Eng. Gas Turbines Power. July 2005; 127(3): 615–620. https://doi.org/10.1115/1.1852563
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