ICME Framework for Damage Assessment and Remaining Creep Life Prediction of In-Service Turbine Blades Manufactured with Ni-Based Superalloys

  • Chao Fu
  • Yadong Chen
  • Siliang He
  • Stoichko Antonov
  • Longfei LiEmail author
  • Weiwei Zheng
  • Qiang FengEmail author
Thematic Section: 5th World Congress on Integrated Computational Materials Engineering
Part of the following topical collections:
  1. 5th World Congress on Integrated Computational Materials Engineering


Accurate creep life prediction is necessary for the evaluation of the remaining creep lives of in-service turbine blades and for the design of new turbine blades in aircraft engines. In this study, an integrated computational material engineering methodology for predicting the remaining creep life of in-service turbine blades was developed by taking a microstructural criterion and creep strain criterion into consideration, and combining artificial neural networks with a modified θ projection model to assess the service temperature, stress, degradation time, and existing creep strain. To explore the application of the method and verify its accuracy, the microstructural degradations at different locations of two directionally solidified superalloy DZ125 turbine blades, which were in-service for 300 h and 980 h in different engines, were characterized and quantified. Using these results, the remaining creep life of the microstructures at different locations of the blade was predicted. Finally, these creep life prediction results were experimentally verified using miniature creep test specimens. The development of this new method provides a reference for the design and service evaluation of turbine blades made of directional solidified and single-crystal Ni-based superalloys.


Turbine blades Ni-based superalloy ICME Remaining creep life prediction Miniature creep test 



The support provided by the National Key Research and Development Program of China (Grant No. 2016YFB0701403), the National Natural Science Foundation of China (Grant No. 51771019 and 51631008) and the 111 Project (No. B170003) is gratefully acknowledged.


  1. 1.
    Antony KC, Goward GW (1988) Aircraft gas turbine blade and vane repair. In: Superalloys 1988, pp 745–754Google Scholar
  2. 2.
    AkeKarlsson S, Persson C, Persson PO (1995) Metallographic approach to hirbine blade life time prediction. Adv Manuf Process 10(5):939–953CrossRefGoogle Scholar
  3. 3.
    Larson FR (1952) A time temperature relationship for rupture and creep stress. Trans ASME 74:765–775Google Scholar
  4. 4.
    Manson SS, Haferd AM (1953) A linear time-temperature relation for extrapolation of creep and stress-rupture data. Technical Note 2890, NACAGoogle Scholar
  5. 5.
    Orr RL, Sherby OD, Dorn JE (1953) Correlations of rupture data for metals at elevated temperatures. Institute of Engineering Research, University of California, BerkeleyCrossRefGoogle Scholar
  6. 6.
    Manson S, Succop G (1956) Stress-rupture properties of Inconel 700 and correlation on the basis of several time-temperature parameters. In: Symposium on metallic materials for service at temperatures above 1600 F, ASTM InternationalGoogle Scholar
  7. 7.
    Wen Z, Hou N, Wang B, Yue Z (2010) Crystallographic life model for single crystal turbine blade and validation by the miniature specimens cut from the turbine blades. Multidiscip Model Mater Struct 6(4):508–529CrossRefGoogle Scholar
  8. 8.
    Dye D, Ma A, Reed RC (2008) Numerical modelling of creep deformation in a CMSX-4 single crystal superalloy turbine blade. In: Superalloys 2008. John Wiley & Sons, Inc., Champion, PA, pp 911–919Google Scholar
  9. 9.
    Pollock TM, Tin S (2006) Nickel-based superalloys for advanced turbine engines: chemistry, microstructure and properties. J Propul Power 22(2):361–374CrossRefGoogle Scholar
  10. 10.
    Reed RC (2008) The superalloys: fundamentals and applications. Cambridge University Press, CambridgeGoogle Scholar
  11. 11.
    Miura N, Kondo Y (2011) Morphology of γ′ precipitates in a first stage low pressure turbine blade of a Ni-based superalloy after service and after following aging. J ASTM Int 9(2):1–9Google Scholar
  12. 12.
    Miura N, Nakata K, Miyazaki M, Hayashi Y, Kondo Y (2010) Morphology of γ′ precipitates in second stage high pressure turbine blade of single crystal nickel-based superalloy after serviced. Mater Sci Forum 638:2291–2296CrossRefGoogle Scholar
  13. 13.
    Lvov G, Levit V, Kaufman M (2004) Mechanism of primary MC carbide decomposition in Ni-base superalloys. Metall Mater Trans A 35(6):1669–1679CrossRefGoogle Scholar
  14. 14.
    Nathal M, MacKay R (1987) The stability of lamellar γ-γ′ structures. Mater Sci Eng 85:127–138CrossRefGoogle Scholar
  15. 15.
    Qin X, Guo J, Yuan C, Chen C, Hou J, Ye H (2008) Decomposition of primary MC carbide and its effects on the fracture behaviors of a cast Ni-base superalloy. Mater Sci Eng A 485(1–2):74–79CrossRefGoogle Scholar
  16. 16.
    Yuan X, Song J, Zheng Y, Huang Q, Yagi K, Xiao C, Feng Q (2016) Abnormal stress rupture property in K465 superalloy caused by microstructural degradation at 975 °C/225 MPa. J Alloy Compd 662:583–592CrossRefGoogle Scholar
  17. 17.
    Cheng K, Jo C, Jin T, Hu Z (2011) Precipitation behavior of μ phase and creep rupture in single crystal superalloy CMSX-4. J Alloy Compd 509(25):7078–7086CrossRefGoogle Scholar
  18. 18.
    Carter TJ (2005) Common failures in gas turbine blades. Eng Fail Anal 12(2):237–247CrossRefGoogle Scholar
  19. 19.
    Dubiel B, Czyrska-Filemonowicz A (2012) TEM analyses of microstructure evolution in Ex-service single crystal CMSX-4 gas turbine blade. Solid State Phenom 186:139–142CrossRefGoogle Scholar
  20. 20.
    Carroll L, Feng Q, Pollock T (2008) Interfacial dislocation networks and creep in directional coarsened Ru-containing nickel-base single-crystal superalloys. Metall Mater Trans A 39(6):1290–1307CrossRefGoogle Scholar
  21. 21.
    Cassenti B, Staroselsky A (2009) The effect of thickness on the creep response of thin-wall single crystal components. Mater Sci Eng A 508(1–2):183–189CrossRefGoogle Scholar
  22. 22.
    Doner M, Heckler JJS (1988) Identification of mechanisms responsible for degradation in thin-wall stress-rupture properties. In: Superalloys 1988, pp 653–662Google Scholar
  23. 23.
    Hüttner R, Gabel J, Glatzel U et al (2009) First creep results on thin-walled single-crystal superalloys. Mater Sci Eng A 510:307–311CrossRefGoogle Scholar
  24. 24.
    Chen Y, Zheng Y, Xiao C, Feng Q (2016) Evaluation of temperature and stress in first stage high pressure turbine blades of a directionally-solidified superalloy DZ125 after service in aeroengines. In: Superalloys 2016. John Wiley & Sons, Inc., Hoboken, NJ, pp 701–710CrossRefGoogle Scholar
  25. 25.
    Chen Y, Zheng Y, Feng Q (2016) Evaluating service temperature field of high pressure turbine blades made of directionally solidified Dz125 superalloy based on micro-structural evolution. Acta Metall Sin 52(12):1545–1556Google Scholar
  26. 26.
    Fu C, Chen Y, Yuan X, Tin S, Antonov S, Yagi K, Feng Q (2019) A modified θ projection model for constant load creep curves-I. Introduction of the model. J Mater Sci Technol 35(1):223–230CrossRefGoogle Scholar
  27. 27.
    Fu C, Chen Y, Yuan X, Tin S, Antonov S, Yagi K, Feng Q (2019) A modified θ projection model for constant load creep curves-II. Application of creep life prediction. J Mater Sci Technol 35(4):687–694CrossRefGoogle Scholar
  28. 28.
    Editorial Board of China Aeronautical Materials Handbook (2005) China aeronautical materials handbook. Standards Press of China, BeijingGoogle Scholar
  29. 29.
    Chunhu T (2008) Failure analysis and prevention for rotor in aero-engine. National Defense Industry Press, BeijingGoogle Scholar
  30. 30.
    Zhang J, Zheng YR, Feng Q (2016) Study on rejuvenation heat treatment of a directionally-solidified superalloy DZ125 damaged by creep. Acta Metall Sin 52(6):717–726Google Scholar
  31. 31.
    Chao F, Chen Y, Li L, Antonov S, Feng Q Exploration of quantitative correlation between microstructures and creep property of a directionally-solidified superalloy using ICME method. J Alloys Compd (under revision)Google Scholar

Copyright information

© The Minerals, Metals & Materials Society 2019

Authors and Affiliations

  1. 1.Beijing Advanced Innovation Center for Materials Genome Engineering, State Key Laboratory for Advanced Metals and MaterialsUniversity of Science and Technology BeijingBeijingChina
  2. 2.Department of General TechnologyChina North Vehicle Research InstituteBeijingChina

Personalised recommendations