PSI - Issue 39

Andrey Shanyavskiy et al. / Procedia Structural Integrity 39 (2022) 327–332 Author name / Structural Integrity Procedia 00 (2019) 000–000

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4. Conclusions In-service fan fracture was realized in the High-Cycle Fatigue regime because the estimated stress level was lower than the elastic limit for VT3–1 titanium alloy (Ti–6Al–3Mo–2Cr alloy). Fatigue fracture of forged fan disk operated on the engine D-18T from the aircraft An-124 and manufactured from VT3–1 titanium alloy was realized with the formation of multiple origins from the geometric stress concentrators as cut in the bottom radial transition of the slot for the blade. The cut of 0.1 mm depth was created during the disk manufacturing procedure. The crack path was performed by the meso-tunneling mechanism with the facetted pattern relief domination. The fatigue crack in the fan disk propagated at the decrease in the equivalent stress level in the direction of fracture surface development. References Tumanov, A.T. (Ed.), 1975. Aircraft Materials, Handbook (in 9 vol.), 1975. VIAM, Moscow (in Russian). Howard, I.C., 1986. Fracture of an Aircraft Horizontal Stabilizer, in “Case Histories Involving Fatigue and Fracture Mechanics” . In: Hudson, C., Rich, T. (Eds.). ASTM International, West Conshohocken, PA, USA, pp. 259–276. Kocanda, D., Kocanda, S., Tomaszek, H., 2001. Probabilistic Description of Fatigue Crack Growth in a Titanium Alloy Notched Member, in “Notch Effects in Fatigue and Fracture. NATO Science Series II: Mathematics, Physics and Chemistry” . In: Pluvinage, G., Gjonaj, M. (Eds.). Springer, Dordrecht, The Netherlands, pp. 239–255. McEvily, A.J., 2004. Failures in inspection procedures: case studies. Eng. Fail. Anal. 11, 167–176. Murakami, Y. (Editor-in-chief), 1987. Stress Intensity Factors Handbook, Vol. 1 and 2. Pergamon Press. Pilchak, A.L., Williams, J.C., 2010. Observations of Facet Formation in Near- α Titanium and Comments on the Role of Hydrogen. Metall. Mater. Trans. A 42, 1000–1027. Pilchak, A.L., 2013. Fatigue Crack Growth Rates in Alpha Titanium: Faceted vs. Striation Growth. Scr. Mater. 68, 277–280. Shanyavskiy, A.A., Stepanov, N.V., 1995. Fractographic Analysis of Fatigue Crack Growth in Engine Compressor Disks of Ti-6Al-3Mo-2Cr Titanium Alloy. Fatigue Fract. Engng Mater. Struct. 18, 539–550. Shanyavskiy, A.A., Losev, A.I., Banov, M.D., 1998. Development of Fatigue Cracking in Aircraft Engine Compressor Disks of Titanium Alloy Ti-6Al-3Mo-2Cr. Fatigue Fract. Eng. Mater. Struct. 21, 297–313. Shanyavskiy, A.A., Losev, A.I., 1999. Fatigue Crack Growth in Aroengine Compressor Disks Made from Titanium Alloy. Fatigue Fract. Engng. Mater. Struct. 22, 949–966. Shanyavskiy, A.A., Losev, A.I., 1999. Synergistic Problem of Introduction of Tolerance Damage Service of Titanium Disks of Aircraft Engines, 8th International Conference on the Mechanical Behaviour of Materials (ICM8). Victoria, BC, Canada, pp. 1227–1232. Shanyavskiy, A., 2003. Tolerance Fatigue Failures of Aircraft Components. Synergetics in Engineering Applications. Monografy, Ufa (in Russian). Shanyavskiy, A.A., 2005. The Effects of Loading Waveform and Microstructure on the Fatigue Response of Ti–6Al–2Sn–4Zn–2Mo Alloy. Fatigue Fract. Eng. Mater. Struct. 28, 195–204. Shanyavskiy, A., 2018. Uniaxial equivalent of stress and stress intensity factor in Mode I crack opening for fatigued metals subjected to multi parametric external loading. MATEC Web Conf 165:13003. https://doi.org/10.1051/matecconf/201816513003 Shanyavskiy, A.A., Soldatenkov, A.P., Nikitin, A.D., 2021. Effect of Wave Process of Plastic Deformation at Forging on the Fatigue Fracture Mechanism of Titanium Compressor Disks of Gas Turbine Engine. Materials 14, 1851. https://doi.org/10.3390/ma14081851 Wanhill, R.J.H., Oldersma, A., 1999. Fatigue and Fracture in an Aircraft Engine Pylon, in “Engineering Against Fatigue” . In: Beynon, J.H., Brown, M.W., Lindley, T.C., Smith, R.A., Tomkins, B. (Eds.). A.A. Balkema: Rotterdam, the Netherlands, pp. 721–727. Williams, J.C., Starke, E.A., Jr., 2003. Progress in Structural Materials for Aerospace Systems. Acta Mater 51, 5775–5799.