Issue 24

A. A. Shanyavskiy, Frattura ed Integrità Strutturale, 24 (2013) 13-25; DOI: 10.3221/IGF-ESIS.24.03 24 In the web, a crack-growth period did not exceed five flights. Yet it achieved 110 flights in the above-mentioned crosspieces. Assuming a once overseen crack likely, the above-mentioned inspection frequencies were introduced. The recommended inspection sequence was introduced up to the disk-shaft joint has been redesigned. The disk to shaft joining was organized by the inner diameter of the discussed disk hub. The reconstructed disk joint to shaft has shown airworthiness for aircrafts with this type of engine without fatigue in-service disks cracking in recommended design service goal. C ONCLUSION 1. In-service turbine disks fatigue cracking of EI437B superalloy in aero-engine NK8-2u of the III stage was considered and LCF regime of their failure was demonstrated. 2. Unified description of fatigue crack growth in metals was applied to stress equivalent  e value estimation based on fatigue striations measurement in fracture surfaces. It was shown that in-service stress  e -level is very high that directed to earlier crack origination by the disk hole-surfaces in bolt-joint than it was designed. 3. Crack growth period for in-service cracked disks was estimated based on fatigue striation spacing measurements. It was discovered one-to-one relation between fatigue striation spacing and crack increment in one flight. 4. Based on crack growth period estimation results, it was recommended in-service non-destructive disks inspection with different intervals in dependence of operating time in service at the moment of developed tests. R EFERENCE [1] Fractography in Failure Analysis. ASTM STP 645, ASTM, Philadelphia, (1978). [2] Failure Analysis and Prevention: Metals Handbook, ASM. Handbook Commit., U.S., 11 (1986). [3] L. Varkoly, J. Zuidema, B. Varkolyova, M. Chalupova, Fatigue failures of materials. TU Delf, Netherlands, (1998) 235. [4] A. A. Shanyavskiy, Tolerance in-service fatigue cracking of aircraft structures. Synergetics in engineering applications. Ufa, Russia, (2003). [5] A. A. Shanyavskiy, In: PROBAMAT- 21st Century: Probabilities and Materials, Ed. K. Franzisconys, Kluwer Academic Publisher, Netherlands, (1998) 11. [6] A. A. Shanyavskiy, In: New results in fatigue and fracture, Eds: W. Kasprzak, E. Macha, V. Panasyuk, M.K. Schaper, Mechanika, Opole-Zakopane, Poland; 1 (300) (2005) 277. [7] A. A. Shanyavskiy, Procedia Engineering, 2(1) (2010) 241. [8] A. Carpinteri, A. Spagnoli, S. Vantadori, Fatigue Fract Engng Mater Struct, 26 (2003) 515. [9] A. A. Shanyavskiy, Fatigue Fract Engng Mater Struct, 19 (1996) 1445. [10] I. V. Demyanushko, I. A. Birger, Mashinostroenie, Moscow, Russia, (1978). [11] I. V. Demyanushko, Yu. M. Temes, Problems of Strength, 4 (1981) 49. [12] A. A. Shanyavskiy, A. I. Losev, M. D. Banov, Fatigue Fract. Engng Mater. Struct., 18 (1998) 539. [13] V. I. Astafiev, D. G. Fedorchenko, L. N. Tzypkaikin, In: Sixth Intern. Fatigue Conf., Fatigue’96, Berlin, 6-10 May, 1 (1996) 499. [14] V. I. Zeitlin, D. G. Fedorchenko, Problems of Strength, 2 (1983) 13. [15] G.J. Lloyd, Fatigue at High temperature, Applied Science Publishers, London, New York, (1983) 187. [16] Y. Murakami, In: Low Cycle Fatigue, Eds. H. D. Solomon, G. R. Halford, L. R. Kaisand, P. Leis, ASTM STP 942, ASTM, Philadelphia, (1986) 1048. [17] Y. Murakami (Ed.) Stress Intensity Factors Handbook, Pergamon Press, Oxford (1987). N OMENCLATURE a minor semi-axis of elliptical fatigue crack c major semi-axis of elliptical fatigue crack da/dN crack-growth rate in the depth direction dc/dN fatigue-crack-growth rate at the specimen surface K I Mode I stress intensity factor