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Journal of Thermal Science

热科学学报

Journal of Thermal Science >

2022 , Vol. 31 >Issue 3: 727 - 740

DOI: https://doi.org/10.1007/s11630-022-1603-z

Heat and mass transfer

Impacts of Startup, Shutdown and Load Variation on Transient Temperature and Thermal Stress Fields within Blades of Gas Turbines

  • CAI Liuxi ,
  • HOU Yanfang ,
  • LI Fang ,
  • LI Yun ,
  • WANG Shunsen ,
  • MAO Jingru
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  • 1. School of Chemical Engineering and Technology, Xi’an Jiaotong University, Xi’an 710049, China
    2. State Key Laboratory of Multiphase Flow in Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China

Online published: 2023-12-01

Supported by

The authors would like to thank the National Natural Science Foundation of China (NSFC) (No. 52076173), the China Postdoctoral Science Foundation (No. 2020M680157), and the Fundamental Research Fund of the Central Universities (No. sxxj032020009) for funding.

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
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Abstract

Based on the actual operation parameters and temperature-dependent material properties of a gas turbine unit, composite cooling blade model and corresponding reliable boundary conditions were established. Transient thermal-fluid-solid coupling simulations were then comprehensively conducted to analyze the transient flow and the temperature field of the blade under startup, shutdown, and variable loads condition. Combined with the obtained transient temperature data, the non-linear finite element method was exploited to examine the effect of these transient operations on the turbine blade thermal stress characteristics. Results show that the temperature and pressure on the blade surface increase with the load level and vice versa. As the startup process progresses, the film cooling effectiveness and the heat convection of airflows inside the blade continuously grow; high-temperature areas on the pressure surface and along the trailing edge of the blade tip gradually disappear. Locally high-temperature zones with the maximum of 1280 K are generated at the air inlet and outlet of the blade platform and the leading edge of the blade tip. The high thermal stresses detected on the higher temperature side of the temperature gradient are commonly generated in places with large temperature gradients and significant geometry variations. For the startup/shutdown process, the rate of increase/decrease of the thermal stress is positively correlated with the load variation rate. A slight variation rate of the load (1.52%/min) can lead to an apparent alteration (41%) to the thermal stress. In operations under action of the variable load, although thermal stress is less sensitive to the load variation, the rising or falling rate of the exerted load still needs to be carefully controlled due to the highly leveled thermal stresses.

Key words： composite cooling blade; thermal-fluid-solid coupling method; transient temperature field; load variation; thermal stress

Cite this article

CAI Liuxi , HOU Yanfang , LI Fang , LI Yun , WANG Shunsen , MAO Jingru . Impacts of Startup, Shutdown and Load Variation on Transient Temperature and Thermal Stress Fields within Blades of Gas Turbines[J]. Journal of Thermal Science, 2022 , 31(3) : 727 -740 . DOI: 10.1007/s11630-022-1603-z

References

[1] Vaferi K., Nekahi S., Vajdi M., et al., Heat transfer, thermal stress and failure analyses in a TiB2 gas turbine stator blade. Ceramics International, 2019, 45(15): 19331–19339.
[2] Rani S., Agrawal A.K., Rastogi V., Failure analysis of a first stage IN738 gas turbine blade tip cracking in a thermal power plant. Case Studies in Engineering Failure Analysis, 2017, 8: 1–10. 
[3] Mishra R.K., Thomas J., Srinivasan K., et al., Failure analysis of an un-cooled turbine blade in an aero gas turbine engine. Engineering Failure Analysis, 2017, 79: 836–844. 
[4] Dong A.H., Yan P.G., Qian X.R., et al., Rotation effect on flow and heat transfer for high-temperature rotor blade in a heavy gas turbine. Journal of Thermal Science, 2021, 30(2): 707–715. 
[5] Vasilyev B., Stress-strain state prediction of high- temperature turbine single crystal blades using developed plasticity and creep models. Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany, Volume 7A: Structures and Dynamics, 2014, Paper No. GT2014-25229.
[6] Brandão P., Infante V., Deus A.M., Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine. Procedia Structural Integrity, 2016, 1: 189–196. 
[7] Salehnasab B., Poursaeidi E., Mortazavi S.A., et al., Hot corrosion failure in the first stage nozzle of a gas  turbine engine. Engineering Failure Analysis, 2016, 60: 316–325. 
[8] Qu S., Fu C.M., Dong C., et al., Failure analysis of the 1st stage blades in gas turbine engine. Engineering Failure Analysis, 2013, 32: 292–303. 
[9] Kargarnejad S., Djavanroodi F., Failure assessment of Nimonic 80A gas turbine blade. Engineering Failure Analysis, 2012, 26: 211–219. 
[10] Khalesi J., Modaresahmadi S., Atefi G., SEM gamma prime observation in a thermal and stress analysis of a first-stage Rene’ 80H gas turbine blade: Numerical and experimental investigation. Iranian Journal of Science and Technology, Transactions of Mechanical Engineering, 2019, 43: 613–626. 
[11] Jafari M.M., Atefi G., Khalesi J., et al., A new conjugate heat transfer method to analyse a 3D steam cooled gas turbine blade with temperature-dependent material properties. Proceedings of the Institution of Mechanical Engineers. Part C, Journal of Mechanical Engineering Science, 2012, 226: 1309–1320. 
[12] Xu N., Liu Z.S., He P., Transient thermal stress analysis of the typical structures in turbine rotor based on thermomechanical analysis. Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany, 2014, Paper No. GT2014-25875.
[13] Farhad S.M., Mohammad V., Amir M., et al., Numerical analyses of heat transfer and thermal stress in a ZrB2 gas turbine stator blade. Ceramics International, 2019, 45: 17742–17750. 
[14] Ou W.H., Yuan Q., Shi Q.X., Life estimation for transient temperature and stress field of heavy-duty gas turbine rotor. China Mechanical Engineering, 2015, 26(7): 929–935.
[15] Krishnakanth P.V., Raju G.N., Prasad R.D.V., et al., Structural & thermal analysis of gas turbine blade by using F.E.M. International Journal of Scientific Research Engineering & Technology, 2013, 2(2): 60–65.
[16] An L., Multi-field coupling simulation of nickel-based alloy turbine blade composite cooling. Harbin Institute of Technology, Harbin, China, 2018. (in Chinese)
[17] Xiao L.W., Strength and life analysis of gas turbine blade based on fluid-thermal-mechanical coupling method. Beijing, University of Chinese Academy of Sciences, China, 2018. (in Chinese)
[18] Tang W.Z., Yang L., Zhu W., et al., Numerical simulation of temperature distribution and thermal stress field in a turbine blade with multilayer-structure TBCs by a fluid-solid coupling method. Journal of Materials Science & Technology, 2016, 32: 452–458.
[19] Bolaina C., Teloxa J., Varela C., et al., Thermomechanical stress distributions in a gas turbine blade under the effect of cooling flow variations. Journal of Turbomachinery- Transactions of the ASME, 2013, 135: 064501. 
[20] Chi Z.R., Liu H.Q., Zang S.H., et al., Conjugate heat transfer optimization of the nonuniform impingement cooling structure of a HPT 2nd stage vane. Proceedings of ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, Montréal, Canada, 2015, Paper No. GT2015-42097.  
[21] Ali K., Anwar O.B., Mohammed E.G., et al., Computational fluid dynamic and thermal stress analysis of coatings for high-temperature corrosion protection of aerospace gas turbine blades. Heat Transfer-Asian Research, 2019, 48: 2302–2328. 
[22] Cai L.X., He Y., Wang S.S., et al., Thermal-fluid-solid coupling analysis on the temperature and thermal Stress field of a nickel-base superalloy turbine blade. Materials, 2021, 14(12): 3315.
[23] Staroselsky A., Martin T.J., Cassenti B., Transient thermal analysis and viscoplastic damage model for life prediction of turbine components. Journal of Engineering for Gas Turbines and Power-Transactions of the ASME, 2015, 137: 042510. 
[24] Zhu J.J., Yang Z.C., Analysis and life cycle prediction of marine gas turbine blades based on thermal-fluid- structure interaction. Chinese Journal of Ship Research, 2010, 5(5): 64–68. 
[25] Menter F.R., Review of the shear-stress transport turbulence model experience from an industrial perspective. International Journal of Computational Fluid Dynamics, 2009, 23(4): 305–316. 
[26] Ho K., Liu J., Elliott T., et al., Conjugate heat transfer analysis for gas turbine film-cooled blade. Proceedings of the ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. Seoul, South Korea. 2016, Paper No. GT2016-56688.
[27] Yu F.L., Shang G.B., Li Y.Y., et al., Numerical investigation on compound cooling effect of the heavy-duty gas turbine first stage blade. Proceedings of the CSEE, 2016, 36(1): 179–186.
[28] Sadegh M.F., Vajdi M., Motallebzadeh A., et al., Numerical analyses of heat transfer and thermal stress in a ZrB2 gas turbine stator blade. Ceramics International. 2019, 45: 17742–17750.
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