Research Papers: Gas Turbines: Turbomachinery

A Damage Evaluation Model of Turbine Blade for Gas Turbine

[+] Author and Article Information
Dengji Zhou, Tingting Wei, Huisheng Zhang, Shixi Ma, Shilie Weng

Gas Turbine Research Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received December 4, 2016; final manuscript received February 5, 2017; published online April 11, 2017. Editor: David Wisler.

J. Eng. Gas Turbines Power 139(9), 092602 (Apr 11, 2017) (9 pages) Paper No: GTP-16-1565; doi: 10.1115/1.4036060 History: Received December 04, 2016; Revised February 05, 2017

Current maintenance, having a great impact on the safety, reliability and economics of a gas turbine, becomes the major obstacle for the application of gas turbines in energy field. An effective solution is to process condition based maintenance (CBM) thoroughly for gas turbines. Maintenance of high temperature blade, accounting for the most of the maintenance costs and time, is the crucial section of gas turbine maintenance. The suggested life of high temperature blade by original equipment manufacturer (OEM) is based on several certain operating conditions, which is used for time based maintenance (TBM). Thus, for the requirement of gas turbine CBM, a damage evaluation model is demanded to estimate the life consumption online. A physics-based model is built, consisting of thermodynamic performance simulation model, stress estimation model, thermal estimation model, and interactive damage analysis model. Unmeasured parameters are simulated by the thermodynamic performance simulation model, as the input of the stress estimation model and the thermal estimation model. Due to the ability to analyze online data, this model can be used to calculate online damage and support CBM decision. Then the stress and temperature distribution of blades will become as the input of the creep damage analysis model and the fatigue damage analysis model. The interactive damage of blades will be evaluated based on the creep and fatigue analysis results. To validate this physics-based model, it is used to calculate the lifes of high temperature blade under several certain operating conditions. And the results are compared to the suggestion value of OEM. An application case is designed to evaluate the application effect of this model. The result shows that the relative error of this model is less than 10.4% in selected cases. And it can cut overhaul costs and increase the availability of gas turbines significantly. Finally, a simple application of this model is proposed to show its functions. The physical-based damage evaluation model proposed in this paper is found to be a useful tool to tracing the online life consumption of a high temperature blade, to support the implementation of CBM for gas turbines, and to guarantee the reliability of gas turbines with lowest maintenance costs.

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Liu, D. Y. , and Zhang, H. P. , 2008, “ Development and Electric Power Generation Technology of the Combustion Turbine,” Appl. Energy Technol., 121(1), pp. 5–8.
Xia, D. , 2008, “ Gas Turbine Diagnostic Theory and Experiment Research Based on Thermal Parameters,” Shanghai Jiao Tong University, Shanghai, China.
Smith, S. H. , and Ghadiali, N. D. , 1983, “ Fatigue Crack Growth Life Evaluation of the Turbine Blades in a Low Pressure Steam Turbine,” Fracture Mechanics: Fourteenth Symposium, Vol. 2, pp. 120–139.
Kobayashi, D. , Miyabe, M. , and Achiwa, M. , 2015, “ Failure Analysis and Life Assessment of Thermal Fatigue Crack Growth in a Nickel-Base Superalloy Based on EBSD Method,” ASME Paper No. GT2015-42425.
Hou, J. , Wicks, B. J. , and Antoniou, R. A. , 2002, “ An Investigation of Fatigue Failures of Turbine Blades in a Gas Turbine Engine by Mechanical Analysis,” Eng. Failure Anal., 9(2), pp. 201–211. [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]
Movaghghar, A. , and Lvov, G. I. , 2012, “ A Method of Estimating Wind Turbine Blade Fatigue Life and Damage Using Continuum Damage Mechanics,” Int. J. Damage Mech., 21(6), pp. 810–821. [CrossRef]
Liu, Z. , Volovoi, V. , and Mavris, D. N. , 2002, “ Probabilistic Remaining Creep Life Assessment for Gas Turbine Components Under Varying Operating Conditions,” AIAA Paper No. AIAA-2002-1277.
Ghafir, M. F. A. , Li, Y. G. , Singh, R. , Huang, K., and Feng, X., 2010, “ Impact of Operating and Health Conditions on Aero Gas Turbine: Hot Section Creep Life Using a Creep Factor Approach,” ASME Paper No. GT2010-22332.
Amaro, R. L. , Antolovich, S. D. , Neu, R. W. , and Fernandez-Zelaia, P., and Hardin, W., 2011, “ Thermomechanical Fatigue and Bithermal–Thermomechanical Fatigue of a Nickel-Base Single Crystal Superalloy,” Int. J. Fatigue, 42, pp. 165–171. [CrossRef]
Yan, X. , and Nie, J. , 2008, “ Creep-Fatigue Tests on Full Scale Directionally Solidified Turbine Blades,” ASME J. Eng. Gas Turbines Power, 130(4), pp. 635–644. [CrossRef]
Wu, X. , and Zhang, Z. , 2015, “ A Mechanism-Based Approach From Low Cycle Fatigue to Thermomechanical Fatigue Life Prediction,” ASME Paper No. GT2015-43974.
Riva, A. , Costa, A. , Dimaggio, D. , Villari, P., Kraemer, K. M., Mueller, F., and Oechsner, M., 2016, “ A Thermo-Mechanical Fatigue Crack Growth Accumulative Model for Gas Turbine Blades and Vanes,” ASME Paper No. GT2016-58053.
Zhou, D. , Mei, J. , Chen, J. , Zhang, H., and Weng, S., 2014, “ Parametric Analysis on Hybrid System of Solid Oxide Fuel Cell and Micro Gas Turbine With CO2 Capture,” ASME J. Fuel Cell Sci. Technol., 11(5), p. 051001. [CrossRef]
Horlock, J. H. , and Torbidoni, L. , 2006, “ Turbine Blade Cooling: The Blade Temperature Distribution,” Proc. Inst. Mech. Eng., Part A, 220(4), pp. 343–353. [CrossRef]
Consonni, S. , 1992, “ Performance Prediction of Gas/Steam Cycles for Power Generation,” Princeton University, Princeton, NJ.
Ainley, D. G. , 1957, “ Internal Air Cooling for Turbine Blades: A General Design Survey,” Aeronautical Research Council Reports and Memo, London, Report No. 3013.
Tao, C. H. , Zhong, P. D. , and Li, R. Z. , 2000, Failure Analysis and Prevention for Rotor in Aero-Engine, National Defence Industry Press, Beijing, China, pp. 102–163.
Liu, S., Wei, C., Pu, X., and Zhang, W., 2012, “ A Modified Analytical Model to Calculate Temperature Distribution of Gas Turbine Blade and the Cooling Air Required,” Proc. CSEE, 32(14), pp. 89–94.
Chiesa, P. , and Macchi, E. , 2004, “ A Thermodynamic Analysis of Different Options to Break 60% Electric Efficiency in Combined Cycle Power Plants,” ASME J. Eng. Gas Turbines Power, 126(4), pp. 770–785. [CrossRef]
Kostyuk, A. , and Frolov, V. , 1988, Steam and Gas Turbines, Mir Publishers, Moscow, Russia.
Haslam, A. S. , and Cookson, R. A. , 2007, “ Lecture Notes of Cranfield University: Mechanical Design of Turbomachinery,” Cranfield University, Cranfield, UK.
Lin, J. W. , 2009, “ Fatigue Life and Reliability Study on Aviation Engine Blade,” Tianjin University, Tianjin, China.
Poursaeidi, E. , Aieneravaie, M. , and Mohammadi, M. R. , 2008, “ Failure Analysis of a Second Stage Blade in a Gas Turbine Engine,” Eng. Failure Anal., 15(8), pp. 1111–1129. [CrossRef]
Lagneborg, R. , and Attermo, R. , 1971, “ The Effect of Combined Low-Cycle Fatigue and Creep on the Life of Austenitic Stainless Steels,” Metall. Trans., 2(7), pp. 1821–1827.
Langer, B. F., 1969, “ Criteria of the ASME Boiler and Pressure Vessel Code for Design by Analysis in Section III and VIII, Division 2,” ASME, New York.
Mazur, Z. , Ortega-Quiroz, G. D. , and García-Illescas, R. , 2012, “ Evaluation of Creep Damage in a Gas Turbine First Stage Blade,” ASME Paper No. ICONE20-POWER2012-55087.
Liu, D. , Li, H. , and Liu, Y. , 2015, “ Numerical Simulation of Creep Damage and Life Prediction of Superalloy Turbine Blade,” Math. Probl. Eng., 2015, pp. 1–10.
Vasilyev, B. E. , and Magerramova, L. A. , 2014, “ High Temperatures Turbine Blades Damage Prediction Taking Into Account Loading History During a Flight Cycle,” 29th Congress of the International Council of the Aeronautical Sciences (ICAS), pp. 1–6.


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Fig. 1

A simplified flow diagram of the online damage evaluation model

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Fig. 2

Scheme of gas turbine simulation model

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Fig. 3

Structure of the high temperature blade of gas turbine

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Fig. 4

Heat transfer in the ith compartment

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Fig. 5

Schematic diagram of the forces on the blade

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Fig. 6

S–N curve of a certain superalloy

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Fig. 7

LMP–stress curve of a certain superalloy

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Fig. 8

Gas turbine configuration of this case study

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Fig. 10

The stress of the back of the first stage rotational blade in the process of cold startup and shutdown

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Fig. 11

The stress of the leading edge of the first stage rotational blade in the process of cold startup and shutdown

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Fig. 9

The stress of the 3/4 height of the first stage NGV in the process of cold startup and shutdown

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Fig. 12

Damage evaluation result of the rotational blade

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Fig. 13

Damage evaluation result of the NGV

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Fig. 14

Effects of power load and fouling extent on damage evaluation result of the rotational blade

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Fig. 15

Cumulative damage process of the rotational blade in the cold startup and shutdown

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Fig. 16

Cumulative damage result of the rotational blade in the process of cold startup and shutdown under different fouling extents




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