journal article·2017-10

Fatigue life prediction based on equivalent initial flaw size for Al-Li alloy 2297 under spectrum loading

Yanzeng Wu, Yaowu Xu, Xiang Guo, Rui Bao

Publisher page

Abstract

Abstract Fatigue life prediction methods based on the Equivalent Initial Flaw Size (EIFS) concept under variable amplitude (VA) spectrum loading conditions were studied in this paper. Fatigue tests of Al-Li alloy 2297 under constant amplitude (CA) and VA loading cases were carried out. Based on the comparison of predictions and test results, different ways to determine the EIFSs and whether the load-interaction effects should be considered in VA fatigue life prediction were discussed to recommend their applicable cases. A good agreement is observed between EIFS model predictions and experimental data, especially in case of high maximum stresses in VA loading.
Source: openaire · Quality: candidate unverified · Source record ↗

Research context

OpenAlex topics: Fatigue and fracture mechanics · Aluminum Alloy Microstructure Properties · Probabilistic and Robust Engineering Design

SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.

References (40)

Show source-provided references
1. Cumulative fatigue damage and life prediction theories: a survey of the state of the art for homogeneous materials10.1016/S0142-1123(97)00081-9 ↗
2. Fatigue life prediction method for the practical engineering use taking in account the effect of the overload blocks10.1016/j.ijfatigue.2016.04.006 ↗
3. Die · Z Ver Dtsch Ing · 1924 · 68 · 339
4. Cumulative damage in fatigue10.1115/1.4009458 ↗
5. Haibach · 1970
6. The prediction of fatigue life in the crack initiation and propagation stages - a state of the art survey10.1016/0013-7944(79)90015-8 ↗
7. Dowling NE, Brose WR, Wilson WK. Notched member fatigue life predication by the local strain approach. SAE: Fatigue under complex loading; 1977. p. 55–84.
8. Schijve · 2009
9. Fatigue damage and crack growth under variable amplitude loading with reference to the counting methods of stress-strain ranges10.1016/j.ijfatigue.2004.09.011 ↗
10. Fatigue crack growth and life predictions under variable amplitude loading for a cast and wrought aluminum alloy10.1016/j.ijfatigue.2005.03.005 ↗
11. Short surface fatigue cracks growth under constant and variable amplitude loading10.1016/j.engfracmech.2009.07.017 ↗
12. Johnson WS, Heller RA, and Yang JN. Flight inspection data and crack initiation times. Proceedings 1977 Annual Reliability and Maintainability Symposium, Philadelphia, PA, January 1977, IEEE Catalog Number 77CH1161-9 ROC, p. 148–154.
13. Rudd · 1976
14. The history, logic and uses of the Equivalent Initial Flaw Size approach to total fatigue life prediction10.1016/j.proeng.2010.03.005 ↗
15. Small crack growth and fatigue life predictions for high-strength aluminium alloys: part I-experimental and fracture mechanics analysis10.1046/j.1460-2695.1998.00080.x ↗
16. Small-crack growth and fatigue life predictions for high-strength aluminium alloys: part II-crack closure and fatigue analyses10.1046/j.1460-2695.2000.00242.x ↗
17. Distribution of equivalent initial flaw size
18. The equivalence of EPS and EIFS based on the same crack growth life data10.1016/j.ijfatigue.2015.05.009 ↗
19. A review of equivalent pre-crack sizes in aluminium alloy 7050–T745110.1111/ffe.12214 ↗
20. Probabilistic fatigue life prediction using an equivalent initial flaw size distribution10.1016/j.ijfatigue.2008.06.005 ↗
21. Crack growth-based fatigue life prediction using an equivalent initial flaw model. Part I: Uniaxial loading10.1016/j.ijfatigue.2009.07.011 ↗
22. Assessment of equivalent initial flaw size estimation methods in fatigue life prediction using compact tension specimen tests10.1016/j.engfracmech.2013.01.007 ↗
23. Analysis approach to durability based on material initial fatigue quality and S-N curve10.1016/S1000-9361(07)60076-4 ↗
24. The behavior of short fatigue cracks and their initiation. Part I: A review of two recent books10.1111/j.1460-2695.1987.tb01150.x ↗
25. A state-of-the-art review on fatigue life prediction methods for metal structures10.1007/s007730200012 ↗
26. Growth behavior of surface cracks in the circumferential plane of solid and hollow cylinders
27. Spectrum loading and crack growth10.1115/1.3425362 ↗
28. Willenborg J, Engle RM, Wood HA. A crack growth retardation model using an effective stress concept. AFFDL-TM-71-1-FBR, Wright Patterson Air Force Laboratory; 1971.10.21236/ADA956517 ↗
29. Elber W. The significance of fatigue crack closure. Am Soc Test Mater 1971:230–242. ASTM STP 486.10.1520/STP26680S ↗
30. Gallagher · 1974
31. Modeling of fatigue crack growth following overloads10.1016/0142-1123(91)90600-4 ↗
32. An engineering model of fatigue crack growth under variable amplitude loading10.1016/j.ijfatigue.2007.03.004 ↗
33. Fracture toughness and fracture modes of aerospace aluminum-lithium alloys
34. AMS4330B. Aluminum alloy, plate (2297–T87) 2.8Cu-1.5Li-0.30Mn-0.12Zr solution heat treated, stretched, and artificially aged. Warrendale, PA: SAE International; 2004.
35. ASTM E466–07. Standard practice for conducting force controlled constant amplitude axial fatigue tests of metallic materials. West Conshohocken, PA: ASTM International; 2007.
36. NASGRO 8.1, Reference Manual (version 8.1, May 2016), Fracture mechanics and fatigue crack growth analysis software, NASA Johnson Space Center and Southwest Research Institute; 2016.
37. Assessment of mixed mode loading on macroscopic fatigue crack paths in thick section Al-Cu-Li alloy plate10.1016/j.matdes.2015.12.116 ↗
38. Fatigue predictions and scatter10.1111/j.1460-2695.1994.tb00239.x ↗
39. Mann JY. Scatter in fatigue life - A materials testing and design problem. In: Sherratt E, Sturgeon JB, editors. Materials, Experimentation and Design in Fatigue. West Bury House; 1981. p. 390–423.
40. Effect of specimen size and notch geometry on equivalent initial flaw size distribution