Prediction of Fatigue Crack Growth Behavior Under Cold-Turbistan Spectrum Loads Using Variable Crack Closure Approach in GTM 720 Nickel Base Superalloy
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Publisher
Springer Nature Singapore
Link
https://link.springer.com/content/pdf/10.1007/978-981-99-4721-8_34
Reference13 articles.
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3. Elber W. The significance of fatigue crack closure, in damage tolerance in aircraft structures, ASTM STP 486. Philadelphia PA: American Society for Testing and Materials; 1971. p. 230–42.
4. Newman JC. Application of a closure model to predict crack growth in three engine disc materials. Int J Fract. 1996;80(2–3):193–218.
5. Manjunatha CM. Fatigue crack growth prediction under spectrum load sequence in an aluminum alloy by K*-RMS Approach. Int J Damage Mech. 2008;17(6):477–92.
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