STRAIN-LIFE ASSESSMENT OF GRAINEX MAR-M 247 FOR NASA’S TURBINE SEAL TEST FACILITY

Content Provider	CiteSeerX
Author	Steinetz, Bruce M. Rimnac, Clare M. Delgado, Irebert R. Halford, Gary R.
Abstract	NASA’s Turbine Seal Test Facility is used to test air-to-air seals for use primarily in advanced jet engine applications. Combinations of high temperature, high speed, and high pressure limit the disk life, due to the concern of crack initiation in the bolt holes of the Grainex Mar-M 247 disk. The primary purpose of this current work is to determine an inspection interval to ensure safe operation. The current work presents high temperature fatigue strain-life data for test specimens cut from an actual Grainex Mar-M 247 disk. Several different strain-life models were compared to the experimental data including the Manson-Hirschberg Method of Universal Slopes, the Halford-Nachtigall Mean Stress Method, and the Modified Morrow Method. The Halford-Nachtigall Method resulted in only an 18 % difference between predicted and experimental results. Using the experimental data at a –99.95 % prediction level and the presence of 6 bolt holes it was found that the disk should be inspected after 665 cycles based on a total strain of 0.5 % at 649 °C.
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