Skip to main content

Advertisement

SpringerLink
Log in

Evaluation of service-induced microstructural damage for directionally solidified turbine blade of aircraft engine

  • Published:
Rare Metals Aims and scope Submit manuscript

Abstract

Turbine blades of gas turbine engines usually suffer from severe operational conditions characterized by high temperature and stress. Severe operational conditions during service cause microstructural changes in turbine blades and degrade their mechanical properties. In this study, service-induced microstructural damages in serviced turbine blades manufactured from a directionally solidified superalloy were evaluated. The observed microstructural damage of the turbine blade mainly involves the coarsening and rafting of γ′ precipitates. The leading edge of 60% height of the turbine blades undergone most severe microstructural damage with significant microstructural evolution at this area. Microstructural damage affects the mechanical properties such as Vickers hardness, that is, Vickers hardness decreases as the equivalent diameter decreases. Microstructural damage shows great position-dependent feature as service temperature and radial stress on blade changes. With the aid of energy-dispersive spectrometer (EDS) analysis on carbide, the transformation of carbide does not exist. In addition, no topological closed-packed phase exists in the turbine blade.

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

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16

Similar content being viewed by others

References

  1. Mazur Z, Luna-Ramirez A, Juárez-Islas JA, Campos-Amezcua A. Failure analysis of a gas turbine blade made of Inconel 738LC alloy. Eng Fail Anal. 2005;12(3):474.

    Google Scholar 

  2. Kargarnejad S, Djavanroodi F. Failure assessment of Nimonic 80A gas turbine blade. Eng Fail Anal. 2012;26(20):211.

    Google Scholar 

  3. Viswanathan R. An investigation of blade failures in combustion turbines. Eng Fail Anal. 2001;8(5):493.

    Google Scholar 

  4. Qu S, Fu CM, Dong C, Tian JF, Zhang ZF. Failure analysis of the 1st stage blades in gas turbine engine. Eng Fail Anal. 2013;32(3):292.

    Google Scholar 

  5. Pollock TM, Tin S. Nickel-based superalloys for advanced turbine engines: chemistry, microstructure and properties. J Propul Power. 2006;22(2):361.

    Google Scholar 

  6. Henderson MB, Arrell D, Larsson R, Heobel M, Marchant G. Nickel based superalloy welding practices for industrial gas turbine applications. Sci Technol Weld Joi. 2004;9(1):13.

    Google Scholar 

  7. Koul AK, Wallace W. Microstructural changes during long time service exposure of udimet 500 and nimonic 115. Metall Trans A. 1983;14(1):183.

    Google Scholar 

  8. Zangeneh S, Farhangi H. Influence of service-induced microstructural changes on the failure of a cobalt-based superalloy first stage nozzle. Mater Des. 2010;31(7):3504.

    Google Scholar 

  9. Maccagno TM, Koul AK, Immarigeon JP, Cutler L, Allem R, L’esperance G. Microstructure, creep properties, and rejuvenation of service-exposed alloy 713C turbine blades. Metall Trans A. 1990;21(12):3115.

    Google Scholar 

  10. Tong JY, Ding XF, Wang ML, Zheng YR, Yagi K, Feng Q. Evaluation of a serviced turbine blade made of GH4033 wrought superalloy. Mater Sci Eng A. 2014;618:605.

    Google Scholar 

  11. Bagci E. Reverse engineering applications for recovery of broken or worn parts and re-manufacturing: three case studies. Adv Eng Soft. 2009;40(6):407.

    Google Scholar 

  12. Bewlay BP, Jackson MR. Method for replacing blade tips of directionally solidified and single crystal turbine blades. U.S. Patent; 5,822,852. 1998.

  13. Ohta Y, Yoshizawa H, Nakagawa YG. Microstructural changes in a Ni-base superalloy during service. Scr Metall. 1989;23(9):1609.

    Google Scholar 

  14. Attarian M, Khoshmanesh R, Nategh S, Davami P. Microstructural evaluation and fracture mechanisms of failed IN-738LC gas turbine blades. Case Stud Eng Fail Anal. 2013;1(2):85.

    Google Scholar 

  15. Jahangiri MR, Abedini M. Effect of long time service exposure on microstructure and mechanical properties of gas turbine vanes made of IN939 alloy. Mater Des. 2014;64(10):588.

    Google Scholar 

  16. McLean M, Tipler HR. Assessment of damage accumulation and property regeneration by hot isostatic pressing and heat treatment of laboratory-tested and service exposed IN 738 LC9. In: Proceedings of the fifth international symposium on superalloys sponsored by the high temperature alloys committee of the metallurgical society of AIME, Superalloys, Pennsylvania; 1984. 73.

  17. Persson C, Persson PO. Evaluation of service-induced damage and restoration of cast turbine blades. J Mater Eng Perform. 1993;2(4):565.

    Google Scholar 

  18. Liu G, Liu L, Han ZH, Zhang GJ, Zhang J. Solidification behavior of Re-and Ru-containing Ni-based single-crystal superalloys with thermal and metallographic analysis. Rare Met. 2017;36(10):792.

    Google Scholar 

  19. Karlsson SA, Persson C, Persson PO. Metallographic approach to hirbine blade life time prediction. Mater Manuf Process. 1995;10(5):939.

    Google Scholar 

  20. Wood MI. The assessment of service induced degradation of nickel based superalloy gas turbine blading. Mater Manuf Process. 1995;10(5):903.

    Google Scholar 

  21. Ray AK, Singh SR, Swaminathan J, Roy PK, Tiwari YN, Bose SC, Ghosh RN. Structure property correlation study of a service exposed first stage turbine blade in a power plant. Mater Sci Eng A. 2006;419(1):225.

    Google Scholar 

  22. Aghaie-Khafri M, Hajjavady M. The effect of thermal exposure on the properties of a Ni-base superalloy. Mater Sci Eng A. 2008;487(1):388.

    Google Scholar 

  23. Holländer D, Kulawinski D, Weidner A, Thiele M, Biermann H, Gampe U. Small-scale specimen testing for fatigue life assessment of service-exposed industrial gas turbine blades. Int J Fatigue. 2016;92:262.

    Google Scholar 

  24. Tong J, Ding X, Wang M, Yagi K, Zheng Y, Feng Q. Assessment of service induced degradation of microstructure and properties in turbine blades made of GH4037 alloy. J Alloys Compd. 2016;657:777.

    Google Scholar 

  25. He YM, Yang JG, Chen SJ, Li Z, Gao ZL. Effect of high-temperature aging on microstructure and mechanical properties of Ni–Mo–Cr based superalloy subjected to simulated heat-affected zone thermal cycle. J Alloys Compd. 2016;660:266.

    Google Scholar 

  26. Sun F, Tong J, Feng Q, Zhang J. Microstructural evolution and deformation features in gas turbine blades operated in-service. J Alloys Compd. 2015;618(618):728.

    Google Scholar 

  27. Wood MI. Gas turbine hot section components: the challenge of ‘residual life’ assessment. Proc Inst Mech Eng A J Power Eng. 2000;214(3):193.

    Google Scholar 

  28. Epishin A, Link T, Nazmy M, Staubli M, Klingelhoffer H, Nolze G. Microstructural degradation of CMSX-4: kinetics and effect on mechanical properties. In: Superalloys, The Minerals. Pennsylvania; 2008. 725.

  29. Yuan XF, Song JX, Zheng YR, Huang Q, Yagi K, Xiao CB, Feng Q. Quantitative microstructural evolution and corresponding stress rupture property of K465 superalloy. Mater Sci Eng A. 2016;651:734.

    Google Scholar 

  30. Yang JX, Zheng Q, Sun XF, Guan HR, Hu ZQ. Morphological evolution of MC carbide in K465 superalloy. J Mater Sci. 2006;41(19):6476.

    Google Scholar 

  31. Cai YL, Zheng YR. Study on the microstructural stability of superalloy K002 and K19H. Chin J Aeronaut. 1980;1(2):89.

    Google Scholar 

  32. Wang C, Guo YA, Guo J, Zhou L. Microstructural changes and their effect on tensile properties of a Ni-Fe based alloy during long-term thermal exposure. Mater Sci Eng A. 2016;670:178.

    Google Scholar 

Download references

Acknowledgements

This study was financially supported by the National Basic Research Program of China (No. 2015CB057401).

Author information

Authors and Affiliations

  1. School of Energy and Power Engineering, Beihang University, Beijing, 100191, China

    Wei-Qing Huang, Xiao-Guang Yang & Shao-Lin Li

  2. Beijing Key Laboratory of Aero-Engine Structure and Strength, Beijing, 100191, China

    Wei-Qing Huang, Xiao-Guang Yang & Shao-Lin Li

Authors
  1. Wei-Qing Huang
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Xiao-Guang Yang
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Shao-Lin Li
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Shao-Lin Li.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Huang, WQ., Yang, XG. & Li, SL. Evaluation of service-induced microstructural damage for directionally solidified turbine blade of aircraft engine. Rare Met. 38, 157–164 (2019). https://doi.org/10.1007/s12598-018-1016-z

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • Issue Date:

  • DOI: https://doi.org/10.1007/s12598-018-1016-z

Keywords

Search

Navigation