Fatigue Investigations of the Compressor Blades with Mechanical Defects

Abstract:

This paper presents results of experimental fatigue analysis of the compressor blades subjected to high cycle fatigue. The blades used in investigations were preliminary defected to simulate the foreign object damage. The blades during experiment were entered into transverse vibration. In results of investigations, the number of cycles to crack initiation and also the crack growth rate were obtained for the blade subjected to transverse vibrations. Moreover, observations of the beach marks on the blade fractures revealed two main shemes of crack propagation process. In this work, the finite element stress analysis of the blade was also performed. Obtrained numerical results shoved that stress level in the notch vicinity is 3 times higher than the stress in the blade without mechanical defects.

• Periodical: Key Engineering Materials (Volume 598)
• Pages: 269-274
• DOI: https://doi.org/10.4028/www.scientific.net/KEM.598.269
• Online since: January 2014
• Authors: Lucjan Witek*
• Keywords: Compressor Blade, Experimental Investigations, Foreign Object Damage (FOD), High Cycle Fatigue (HCF), Resonant Vibrations

References

[1] S.R. Thompson, J.J. Ruschau, T. Nicholas, Influence of residual stresses on high cycle fatigue strength of Ti–6Al–4V subjected to foreign object damage, International Journal of Fatigue 23 (2001) 405–412.

DOI: 10.1016/s0142-1123(01)00166-9

[2] J.O. Peters, R.O. Ritchie, Influence of foreign-object damage on crack initiation and early crack growth during high-cycle fatigue of Ti–6Al– 4V, Engineering Fracture Mechanics 67 (2000) 193–207.

DOI: 10.1016/s0013-7944(00)00045-x

[3] D. Nowell, D. Dini, P. Duo, Stress analysis of V-notches with and without cracks, with application to foreign object damage, Journal of Strain Analysis 38 (2003), 1–13.

DOI: 10.1243/03093240360713487

[4] L. Witek, Numerical stress and crack initiation analysis of the compressor blades after foreign object damage subjected to high-cycle fatigue, Engineering Failure Analysis 18 (2011) 2111-2125.

DOI: 10.1016/j.engfailanal.2011.07.002

[5] L. Witek, Crack propagation analysis of mechanically damaged compressor blades subjected to high cycle fatigue, Engineering Failure Analysis 18 (2011) 1223–1232.

DOI: 10.1016/j.engfailanal.2011.03.003

[6] L. Witek, Fatigue analysis of the compressor blades with v-notches, in: Structural Integrity: Influence of efficiency and green imperatives, Springer, Montreal, 2011, pp.721-734.

DOI: 10.1007/978-94-007-1664-3_57

[7] L. Witek, Stress intensity factor calculations for the compressor blade with half-elliptical surface crack using Raju-Newman solution, in: Fatigue of Aircraft Structures Monographic Series, Versita, Warsaw, 2011, 153-164.

DOI: 10.2478/v10164-010-0046-2

[8] L. Witek, M. Orkisz, P. Wygonik et al. Fracture analysis of a turbine casing, Engineering Failure Analysis 18 (2011) 914-923.

DOI: 10.1016/j.engfailanal.2010.11.005

[9] L. Witek, Failure analysis of the wing-fuselage connector of an agricultural aircraft, Engineering Failure Analysis 13 (2006) 572-581.

DOI: 10.1016/j.engfailanal.2004.12.029

[10] P. B. Michailov, Sprawocznik po metaliczeskim matierialam turbino- i motorostroenija, Sankt Petersburg, 1961.

[11] MSC-PATRAN-2004 Users Manual, MSC Corporation, Los Angeles, 2004.

[12] ABAQUS ver. 6.9 Users Manual, Abaqus Inc., 2009.

[13] M. Wierzbińska, A.  Poznańska, L. Witek, Fracture analysis of compressor blade of a helicopter engine, Engineering Failure Analysis 16 (2009) 1616-1622.

DOI: 10.1016/j.engfailanal.2008.10.022