Skip to main content
SpringerLink
Log in

Very-High-Cycle-Fatigue of in-service air-engine blades, compressor and turbine

  • Article
  • Special Topic: Airworthiness and Fatigue
  • Published:
Science China Physics, Mechanics and Astronomy Aims and scope Submit manuscript

Abstract

In-service Very-High-Cycle-Fatigue (VHCF) regime of compressor vane and turbine rotor blades of the Al-based alloy VD-17 and superalloy GS6K, respectively, was considered. Surface crack origination occurred at the lifetime more than 1500 hours for vanes and after 550 hours for turbine blades. Performed fractographic investigations have shown that subsurface crack origination in vanes took place inspite of corrosion pittings on the blade surface. This material behavior reflected lifetime limit that was reached by the criterion VHCF. In superalloy GS6K subsurface fatigue cracking took place with the appearance of flat facet. This phenomenon was discussed and compared with specimens cracking of the same superalloy but prepared by the powder technology. In turbine blades VHCF regime appeared because of resonance of blades under the influenced gas stream. Both cases of compressor-vanes and turbine blades in-service cracking were discussed with crack growth period and stress equivalent estimations. Recommendations to continue aircrafts airworthiness were made for in-service blades.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Similar content being viewed by others

Abbreviations

a :

crack length in the depth

area :

area of crack origination zone

c :

crack length by the surface of the semi-elliptically-shaped crack

h 1 :

spacing of meso-beach-marks 1 (MBM1)

HV :

Vickers hardness

N f :

number of cycles to failure (durability)

(N p)1 :

crack growth period calculated based on spacing of beach-marks MBM1

(Δ q σ) i :

range of stress for bifurcation area of S-N curves

ɛ :

tensile deformation

λ :

ratio of biaxial cyclic stresses (σ2/σ1)

σ a :

stress amplitude

(σ e)1 :

tensile stress equivalent value

σ U :

ultimate tensile stress

σ 0.2 :

0.2% offset yield strength

σ 1 :

tensile stress opening the fatigue crack

σ 2 :

tensile or compressive stress acting in a perpendicular direction to the

σ1 :

direction

σ i :

tensile stress opening the fatigue crack

σ wi :

mean stress for bifurcation i-area

References

  1. Shanyavskiy A A. Tolerance fatigue cracking of in-service aircraft structures. In: Synergetics in Engineering Application. Ufa, Russia: Publishing House of Scientific and Technical Literature Monography, 2003. 566–628

    Google Scholar 

  2. Shanyavskiy A A. Fatigue limit—Material property as an opened or closed system? Practical view on the aircraft components failures in GCF area. Int J Fatigue, 2006, 28: 1647–1657

    Article  MATH  Google Scholar 

  3. Shanyavskiy A A. Modeling of metals fatigue cracking. In: Synergetics in Aviation. Ufa, Russia: Publishing House of Scientific and Technical Literature Monograph, 2007. 284–498

    Google Scholar 

  4. Shanyavskiy A A. Bifurcation diagram for in-service fatigued metals. Proc Eng, 2010, 2(1): 241–251

    Article  Google Scholar 

  5. Shanyavsky A A. Synergetical models of fatigue-surface appearance in metals: The scale levels of self-organization, the rotation effects, and density of fracture energy. In: Frantsiskony, ed. PROBAMAT-21st Century: Probabilities and Materials. Netherlands: Kluwer Academic Publisher, 1998. 11–44

    Chapter  Google Scholar 

  6. Ivanova V S. Synergetics, Strength and Fracture of Metallic Materials. Cambridge: Cambridge International Science Publishing, 1998. 26–74

    Google Scholar 

  7. Murakami Y. Metal Fatigue: Effects of Small Defects and Nonmetallic Inclusions. Oxford: Elsevier, 2002. 56–89

    Google Scholar 

  8. Sakai T, Ochi Y. Very high cycle fatigue. In: Proc. Third Intern Conf VHCF-3, September 16–19, 2004, Ritsumeikan University, Kusatsu, Japan, 2004. 40–208

    Google Scholar 

  9. Bathias C, Paris P C. Gigacycle fatigue in mechanical practice. Marcel Dekker, NY, USA, 2005. 87–257

    Google Scholar 

  10. Berger C, Christ H J. Very high cycle fatigue (VHCF 5). In: Proc. Int. Conf. VHCF5, DVM, June 28–30, 2011, Berlin, Germany, 2011. 59–107

    Google Scholar 

  11. Shanyavskiy A A, Potapenko Yu. In-service very-high-cycle-fatigue of titanium compressor blades of aircraft engines. In: Allison J E, Jones J W, Larsen J M, Ritchie R O, eds. Proceeding of Fourth Int. Conf. on Very High Cycle Fatigue (VHCF-4), TMS, USA, 2007. 163–168

    Google Scholar 

  12. Palin-Luk T, Perez-Mora R, Bathias C, et al. Fatigue crack initiation and growth on steel in very high cycle regime with sea corrosion. Eng Fracture Mech, 2010, 77: 1953–1962

    Article  Google Scholar 

  13. Shanyavskiy A A, Koltsun Y I. Near-bifurcation fatigue cracking of the surface-hardened and notched metallic rods. In: Yates J R, ed. Proceedings of Int. Conf. “Fatigue 2007”, Cambridge, UK, 2007. 235–241 (CD)

    Google Scholar 

  14. Shanyavskiy A. Mechanisms of the 2024-T351 Al-Alloy fatigue cracking in bifurcation area after laser shocks hardening procedure. Key Eng Mater, 2011, 465: 511–514

    Article  Google Scholar 

  15. Shanyavskiy A A. Fatigue cracking of smooth and notched specimens of compacted superalloy EP741 NP in high- and very-high-cycle-fatigue regime. In: Berger C, Christ H-J, eds. Proceeding of Int. Conf. VHCF5, DVM, June 28–30, 2011, Berlin, Germany 2011. 107–112

    Google Scholar 

  16. Shanyavskiy A, Banov M. The twisting mechanism of subsurface fatigue cracking in Ti-6Al-2Sn-4Zr-2Mo-0.1Si alloy. Eng Fracture Mech, 2010, 77: 1896–1906

    Article  Google Scholar 

  17. Birger I A, Shorr B F, Iosilevich U B. Strength calculation for structures. Moscow, Mashinostroenie, 1993. 287–295

    Google Scholar 

  18. McEvily A J, Endo M. A method for the prediction of the influence of flaws on the fatigue strength under biaxial loading. In: Sonsino C M, Zenneer H, Portella P D, eds. Proceedings of Seventh Intern. Conf. Biaxial/Multiaxial Fatigue Fract., June 28–July 1, Berlin, Germany, 2004. 247–252

    Google Scholar 

Download references

Author information

Authors and Affiliations

  1. State Centre for Flights Safety, Airport Sheremetievo-1, PO Box 54, Moscow Region, Chimkinskiy State, 141426, Russia

    A. A. Shanyavskiy

Authors
  1. A. A. Shanyavskiy
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to A. A. Shanyavskiy.

Rights and permissions

Reprints and permissions

About this article

Cite this article

Shanyavskiy, A.A. Very-High-Cycle-Fatigue of in-service air-engine blades, compressor and turbine. Sci. China Phys. Mech. Astron. 57, 19–29 (2014). https://doi.org/10.1007/s11433-013-5364-2

Download citation

  • Received:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s11433-013-5364-2

Keywords

Search

Navigation