Research Papers

Crack Growth Behavior of Full-Scale Turbine Attachment Under Combined High and Low Cycle Fatigue

[+] Author and Article Information
Dianyin Hu

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beijing 100191, China;
Beijing Key Laboratory of Aero-Engine
Structure and Strength,
Beijing 100191, China

Lin Yan, Ye Gao, Jianxing Mao

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

Rongqiao Wang

School of Energy and Power Engineering,
Beihang University,
Beijing 100191, China;
Collaborative Innovation Center of
Advanced Aero-Engine,
Beijing 100191, China;
Beijing Key Laboratory of Aero-Engine
Structure and Strength,
Beijing 100191, China
e-mail: wangrq@buaa.edu.cn

1Corresponding author.

Manuscript received February 28, 2018; final manuscript received March 27, 2019; published online May 6, 2019. Assoc. Editor: Damian M. Vogt.

J. Eng. Gas Turbines Power 141(9), 091002 (May 06, 2019) (10 pages) Paper No: GTP-18-1102; doi: 10.1115/1.4043555 History: Received February 28, 2018; Revised March 27, 2019

Turbine attachments in the aero-engine are generally subjected to combined high and low cycle fatigue (CCF) loadings, i.e., low cycle fatigue (LCF) loading due to centrifugal and thermal loading stresses superimposed to the aerodynamically induced high cycle fatigue (HCF) loading. The primary focus of this study is to predict the crack growth life for the actual full-scale turbine attachment through experimentally examining the crack growth behavior under CCF loading at elevated temperature. The crack closure effect was first investigated by using the corner-notched (CN) specimen cut from the turbine attachment since the stress state of CN specimen is more similar to turbine attachment than compact tension (CT) specimen. Employing digital image correlation (DIC) technique, the level of crack closure of CN specimen was clarified under different stress ratios (R) for LCF loading. Afterward, a CCF crack growth model for the full-scale turbine attachment was proposed, which takes the crack closure effect, time-independent crack increment, and transient vibrational analysis into account. In order to verify the proposed method, a Ferris wheel system was established to conduct CCF test on the full-scale turbine attachment at elevated temperature. This study provides an effective methodology to predict the fatigue crack growth (FCG) life of full-scale turbine attachment under CCF loading.

Copyright © 2019 by ASME
Your Session has timed out. Please sign back in to continue.


Hu, D. , Meng, F. , Liu, H. , Song, J. , and Wang, R. , 2016, “ Experimental Investigation of Fatigue Crack Growth Behavior of GH2036 Under Combined High and Low Cycle Fatigue,” Int. J. Fatigue., 85, pp. 1–10. [CrossRef]
Padula, S. A. , II , Shyam, A. , Ritchie, R. O. , and Milligan, W. W. , 1999, “ High Frequency Fatigue Crack Propagation Behavior of a Nickel-Base Turbine Disk Alloy,” Int. J. Fatigue, 21(7), pp. 725–731. [CrossRef]
Hu, D. , Yang, Q. , Liu, H. , Mao, J. , Meng, F. , Wang, Y. , Ren, M. , and Wang, R. , 2017, “ Crack Closure Effect and Crack Growth Behavior in GH2036 Superalloy Plates Under Combined High and Low Cycle Fatigue,” Int. J. Fatigue, 95, pp. 90–103. [CrossRef]
He, D. , Lin, Y. C. , Chen, M. , and Li, L. , 2017, “ Kinetics Equations and Microstructural Evolution During Metadynamic Recrystallization in a Nickel-Based Superalloy With δ Phase,” J. Alloy Compd., 690, pp. 971–978. [CrossRef]
Lin, Y. C. , Deng, J. , Jiang, Y. , Wen, D. , and Liu, G. , 2014, “ Hot Tensile Deformation Behaviors and Fracture Characteristics of a Typical Ni-Based Superalloy,” Mater Des., 55, pp. 949–957. [CrossRef]
Lin, Y. C. , Chen, X. M. , Chen, M. S. , Zhou, Y. , Wen, D. X. , and He, D. G. , 2016, “ A New Method to Predict the Metadynamic Recrystallization Behavior in a Typical Nickel-Based Superalloy,” Appl. Phys. A, 122(6), p. 601. [CrossRef]
Deng, G.-J. , Tu, S.-T. , Zhang, X.-C. , Wang, J. , Zhang, C.-C. , Qian, X.-Y. , and Wang, Y.-N. , 2016, “ Small Fatigue Crack Initiation and Growth Mechanisms of Nickel-Based Superalloy GH4169 at 650 °C in Air,” Eng. Fract. Mech., 153, pp. 35–49. [CrossRef]
Wolf, E. , 1970, “ Fatigue Crack Closure Under Cyclic Tension,” Eng. Fract. Mech., 2(1), pp. 37–45. [CrossRef]
de Matos, P. F. P. , and Nowell, D. , 2009, “ Experimental and Numerical Investigation of Thickness Effects in Plasticity-Induced Fatigue Crack Closure,” Int. J. Fatigue, 31(11–12), pp. 1795–1804. [CrossRef]
Shankar, K. , and Wu, W. , 2002, “ Effect of Welding and Weld Repair on Crack Propagation Behaviour in Aluminium Alloy 5083 Plates,” Mater Des., 23(2), pp. 201–208. [CrossRef]
Newman, J. , 1981, “ A Crack-Closure Model for Predicting Fatigue Crack Growth Under Aircraft Spectrum Loading,” STP748-EB Methods and Models for Predicting Fatigue Crack Growth Under Random Loading, ASTM International, West Conshohocken, PA, pp. 53–84.
Liu, H. , Shang, D. , Liu, J. , and Guo, Z. , 2015, “ Fatigue Life Prediction Based on Crack Closure for 6156 Al-Alloy Laser Welded Joints Under Variable Amplitude Loading,” Int. J. Fatigue, 72, pp. 11–18. [CrossRef]
McClung, R. , Thacker, B. , and Roy, S. , 1991, “ Finite Element Visualization of Fatigue Crack Closure in Plane Stress and Plane Strain,” Int. J. Fract., 50(1), pp. 27–49.
Powell, B. E. , 1995, “ Fatigue Crack Growth Behaviour of Two Contrasting Titanium Alloys,” Int. J. Fatigue, 17(3), pp. 221–227. [CrossRef]
Powell, B. E. , Hawkyard, M. , and Grabowski, L. , 1997, “ The Growth of Cracks in Ti-6Al-4V Plate Under Combined High and Low Cycle Fatigue,” Int. J. Fatigue, 19(93), pp. 167–176. [CrossRef]
Schweizer, C. , Seifert, T. , Nieweg, B. , von Hartrott, P. , and Riedel, H. , 2011, “ Mechanisms and Modelling of Fatigue Crack Growth Under Combined Low and High Cycle Fatigue Loading,” Int. J. Fatigue, 33(2), pp. 194–202. [CrossRef]
Hou, N. X. , Wen, Z. X. , Yu, Q. M. , and Yue, Z. F. , 2009, “ Application of a Combined High and Low Cycle Fatigue Life Model on Life Prediction of SC Blade,” Int. J. Fatigue, 31(4), pp. 616–619. [CrossRef]
Zhu, S. , Yue, P. , Yu, Z. , and Wang, Q. , 2017, “ A Combined High and Low Cycle Fatigue Model for Life Prediction of Turbine Blades,” Materials, 10(7), pp. 698–712. [CrossRef]
Oakley, S. Y. , and Nowell, D. , 2007, “ Prediction of the Combined High- and Low-Cycle Fatigue Performance of Gas Turbine Blades After Foreign Object Damage,” Int. J. Fatigue, 29(1), pp. 69–80. [CrossRef]
Patriarca, L. , Foletti, S. , Beretta, S. , Parodi, S. , and Riva, A. , 2017, “ Crack Propagation Under Combined Cycle Fatigue for a Precipitation Hardened Steel,” Procedia Struct. Integr., 7, pp. 214–221. [CrossRef]
Holycross, C. M. , Shen, M. H. H. , Scott-Emuakpor, O. E. , and George, T. J. , 2013, “ Energy-Based Fatigue Life Prediction Combined Low Cycle High Cycle Fatigue,” ASME Paper No. GT2013-95785.
Zheng, X. , Engler-Pinto, C. C. , Su, X. , Cui, H. , and Wen, W. , 2013, “ Modeling of Fatigue Damage Under Superimposed High-Cycle and Low-Cycle Fatigue Loading for a Cast Aluminum Alloy,” Mater. Sci. Eng. A., 560, pp. 792–801. [CrossRef]
Karunananda, K. , Ohga, M. , Dissanayake, R. , and Siriwardane, S. , 2010, “ A Combined High and Low Cycle Fatigue Model to Estimate Life of Steel Bridges,” J. Eng. Technol. Res., 2(8), pp. 144–160.
Chondros, T. G. , and Dimarogonas, A. D. , 1979, “ Identification of Cracks in Circular Plates Welded at the Contour,” ASME Paper No. 79-DET-106.
Rizos, P. F. , Aspragathos, N. , and Dimarogonas, A. D. , 1990, “ Identification of Crack Location and Magnitude in a Cantilever Beam From the Vibration Modes,” J. Sound Vib., 138(3), pp. 381–388. [CrossRef]
Dentsoras, A. J. , and Kouvaritakis, E. P. , 1995, “ Effects of Vibration Frequency on Fatigue Crack Propagation of a Polymer at Resonance,” Eng. Fract. Mech., 50(4), pp. 467–473. [CrossRef]
Wauer, J. , 1990, “ On the Dynamics of Cracked Rotors: A Literature Survey,” ASME Appl. Mech. Rev., 43(1), pp. 13–17. [CrossRef]
Dimarogonas, A. D. , Paipetis, S. A. , and Chondros, T. G. , 2013, Variational Formulation of Consistent: Continuous Cracked Structural Members. Analytical Methods in Rotor Dynamics, 2nd ed., Springer, Dordrecht, The Netherlands, pp. 221–250.
ASTM, 2013, “ Standard Test Method for Measurement of Fatigue Crack Growth Rates,” ASTM International, West Conshohocken, PA, Standard No. ASTM E647-13.
Newman, J. C. , and Raju, I. S. , 1983, “ Stress Intensity Factor Equations for Cracks in Three-Dimensional Finite Bodies Subjected to Tension and Bending Loads,” National Aeronautics and Space Administration, Langley Research Center, Springfield, VA, NASA Technical Memorandum 85793.
Pickard, A. C. , 1986, The Application of 3-Dimensional Finite Element Methods to Fracture Mechanics and Fatigue Life Prediction, Chameleon Press, London.
Vasco-Olmo, J. M. , James, M. N. , Christopher, C. J. , Patterson, E. A. , and Díaz, F. A. , 2016, “ Assessment of Crack Tip Plastic Zone Size and Shape and Its Influence on Crack Tip Shielding,” Fatigue Fract. Eng. Mater. Struct., 39(8), pp. 969–981. [CrossRef]
Wang, R. , and Nie, J. , 1997, “ A New Experimental Method to Study Combined Fatigue of Actual Turbine Disk Mortise Teeth at Elevated Temperatures,” ASME J. Eng. Gas Turbines Power, 119(4), pp. 969–972. [CrossRef]
Hu, D. , and Wang, R. , 2013, “ Combined Fatigue Experiments on Full Scale Turbine Components,” Aircr. Eng. Aerosp. Technol., 85(1), pp. 4–9. [CrossRef]
Liu, H. , Hu, D. , Wang, R. , Shen, X. , and Fan, J. , 2014, “ Fatigue Crack Growth of Multiple Load Path Structure Under Combined Fatigue Loading—Part II: Experiment Study,” ASME Paper No. GT2014-26681.
Zitounis, V. , 2003, “ Fatigue Crack Growth Rates Under Variable Amplitude Load Spectra Containing Tensile Underloads,” Ph.D. thesis, Cranfield University, Cranfield, UK.
Hu, D. , Wei, J. , Liu, H. , Si, W. , and Wang, R. , 2014, “ Fatigue Crack Growth of Multiple Load Path Structure Under Combined Fatigue Loading—Part I: Numerical Simulation,” ASME Paper No. GT2014-25719.


Grahic Jump Location
Fig. 1

The geometries of (a) CN specimen, (b) turbine disk, (c) turbine blade, and (d) assembly sketch of the turbine attachment (unit: mm)

Grahic Jump Location
Fig. 2

Precrack at the third tooth of turbine attachment

Grahic Jump Location
Fig. 3

Geometric parameters of corner crack on the cross section of the specimen

Grahic Jump Location
Fig. 4

Sketches of the CCF test system for full-scale turbine attachment: (a) constituent parts of the Ferris wheel system test system and (b) loading method: 1—upper jointer for LCF loading, 2—upper load-transmission pin, 3—drawplate, 4—hold-down bolt 1, 5—blade clamp, 6—rolling bearing 1, 7—left load-transmission plate, 8—heating coil 1, 9—part of actual turbine disk, 10—lower jointer for LCF loading, 11—lower load-transmission pin, 12—rolling bearing 2, 13—load-bearing bar, 14—right load-transmission plate, 15—actual turbine blade, and 16—vibration point

Grahic Jump Location
Fig. 5

FCG results of GH2036 superalloy under different stress ratios for CN specimens

Grahic Jump Location
Fig. 6

Variation of load and COD with frame number at crack length a =4.0 mm under stress ratios at (a) R =0.1, (b) R =0.4, and (c) R =0.7 for CN and plate specimen

Grahic Jump Location
Fig. 7

Comparison of normalized crack opening SIF Kop using DIC measurement at different stress ratio

Grahic Jump Location
Fig. 8

CCF crack propagation life prediction framework for turbine attachment subjected to CCF loading

Grahic Jump Location
Fig. 9

Typical failure of turbine attachment after CCF test

Grahic Jump Location
Fig. 10

Fracture surface of (a) CN specimen under LCF loading, which is for crack closure level study, and (b) turbine attachment under CCF loading

Grahic Jump Location
Fig. 11

Crack propagation mode in (a) plated specimen and (b) turbine attachment under CCF loading

Grahic Jump Location
Fig. 12

(a) Meshes of the turbine component, and FEM results of vibrational stress distribution at different crack length, (b) 1.0 mm × 1.0 mm, and (c) 2.0 mm × 2.0 mm

Grahic Jump Location
Fig. 13

Comparisons between the experimental and predicted crack growth life of full-scale turbine attachment under CCF loading including (a) crack length versus crack growth life and (b) predicted life versus experimental life



Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In