Chinese

Journal of Thermal Science

热科学学报

Journal of Thermal Science >

2024 , Vol. 33 >Issue 1: 172 - 189

DOI: https://doi.org/10.1007/s11630-023-1904-x

Comparative Study on Different Methods for Prediction of Thermal Insulation Performance of Thermal Barrier Coating Used on Turbine Blades

  • ZHANG Zhixin ,
  • ZENG Wu ,
  • ZHANG Xiaodong ,
  • ZENG Yuntao
Expand
  • 1. Advanced Gas Turbine Laboratory, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    2. Key Laboratory of Advanced Energy and Power, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
    3. Innovation Academy for Light-duty Gas Turbine, Chinese Academy of Sciences, Beijing 100190, China
    4. University of Chinese Academy of Sciences, Beijing 100049, China

Online published: 2024-01-16

Supported by

This work has been supported by National Science and Technology Major Project (Grand No. J2019-IV-0006-0074) and National Science and Technology Major Project (Grand No. J2019-II-0010-0030).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2023
Fold

Abstract

As turbine inlet temperature gets higher and higher, thermal barrier coating (TBC) is more and more widely used in turbine blades. For turbine blades with TBC, it is of great significance to evaluate the temperature distribution of its substrate metal quickly and accurately, especially during the design stage. With different degrees of simplification such as whether to consider the change of the geometric size of the fluid domain by TBC and whether to consider the planar heat conduction in TBC, three different methods used in conjugate heat transfer (CHT) simulation to model the TBC of the turbine blades have been developed and widely used by researchers. However, little research has been conducted to investigate the influence of the three methods on the temperature distribution of turbine blade. To fill this gap, three geometric models were designed. They are a solid conduction model with a substrate metal layer and a TBC layer, a transonic turbine vane with internal cooling and TBC, and a plate cylindrical film hole cooling model with TBC. Different methods were used in these geometric models and their differences were carefully analyzed and discussed. The result shows that for the conduction model used in this paper, with the same TBC surface temperature distribution, the difference between the three methods is very small and can be ignored. For a transonic turbine vane with internal cooling, regarding the local maximum temperature of the substrate-TBC interface, the largest difference between the method in which TBC is considered as a thermal resistance or a virtual layer of cells and the method in which three-dimensional heat conduction equation of TBC is solved occurs at the trailing edge. The difference near the leading edge is below 2 K. When employed to the film cooling model, the difference of the laterally averaged temperature of the substrate-TBC interface can be 8 K which is mainly due to the change of the length to diameter ratio of the film cooling hole by TBC. If the substrate thickness is reduced by the thickness of TBC when three-dimensional heat conduction equation of TBC is solved, the temperature difference between the three methods will be quite limited.

Key words： turbine blade; thermal barrier coating; conjugate heat transfer; film cooling hole

Cite this article

ZHANG Zhixin , ZENG Wu , ZHANG Xiaodong , ZENG Yuntao . Comparative Study on Different Methods for Prediction of Thermal Insulation Performance of Thermal Barrier Coating Used on Turbine Blades[J]. Journal of Thermal Science, 2024 , 33(1) : 172 -189 . DOI: 10.1007/s11630-023-1904-x

References

[1] Clarke D.R., Oechsner M., Padture N.P., Thermal-barrier coatings for more efficient gas-turbine engines. MRS Bulletin, 2012, 37(10): 891–898.
[2] Padture N.P., Gell M., Jordan E.H., Thermal barrier coatings for gas-turbine engine applications. Science, 2002, 296(5566): 280–284.
[3] Rao Y., Liu Y., Wan C., Multiple-jet impingement heat transfer in double-wall cooling structures with pin fins and effusion holes. International Journal of Thermal Sciences, 2018, 133: 106–119.
[4] Zhang H., Zou Z., Li Y., et al., Conjugate heat transfer investigations of turbine vane based on transition models. Chinese Journal of Aeronautics, 2013, 26(4): 890–897.
[5] Wang P., Li Y., Zou Z., et al., Conjugate heat transfer investigation of cooled turbine using the preconditioned density-based algorithm. Propulsion and Power Research, 2013, 2(1): 56–69.
[6] Jiang J., Jiang L., Cai Z., et al., Numerical stress analysis of the TBC-film cooling system under operating conditions considering the effects of thermal gradient and TGO growth. Surface and Coatings Technology, 2019, 357: 433–444.
[7] Wang H., Fan F.S., Pu J., et al., Flow and heat transfer characteristics of round-hole film cooling with crater. Journal of Aerospace Power, 2022, 37(3): 492–501.
[8] Meng Z., Liu Y., Li Y., et al., A study on cooling performance of surface-modified TBC-film cooling system with bio-inspired micro-riblets. International Journal of Thermal Sciences, 2022, 172: 107340.
[9] Ziaei-Asl A., Ramezanlou M.T., Thermo-mechanical behavior of gas turbine blade equipped with cooling ducts and protective coating with different thicknesses. International Journal of Mechanical Sciences, 2019, 150: 656–664.
[10] Zhu W., Wang J.W., Yang L., et al., Modeling and simulation of the temperature and stress fields in a 3D turbine blade coated with thermal barrier coatings. Surface and Coatings Technology, 2017, 315: 443–453.
[11] Mensch A., Thole K.A., Craven B.A., Conjugate heat transfer measurements and predictions of a blade endwall with a thermal barrier coating. Journal of Turbomachinery, 2014, 136(12): 121003.
[12] Reyhani M.R., Alizadeh M., Fathi A., et al., Turbine blade temperature calculation and life estimation-a sensitivity analysis. Propulsion and Power Research, 2013, 2(2): 148–161.
[13] Alizadeh M., Izadi A., Fathi A., Sensitivity analysis on turbine blade temperature distribution using conjugate heat transfer simulation. Journal of Turbomachinery, 2014, 136(1): 011001.
[14] Takahashi T., Watanabe K., Fujii T., et al., Numerical analysis of temperature distribution of a film-cooled and TBC coated blade. ASME Turbo Expo 2008: Power for Land, Sea, and Air, Berlin, Germany, 2008, Paper No. GT2008-50730.
[15] Hu B.C., Wang J.H., Xu H.Z., et al., Numerical investigation of a thermal barrier coated vane using conjugate heat transfer approach. Journal of Aerospace Power, 2017, 32(10): 2394–2402.
[16] Prapamonthon P., Xu H., Yang W., et al., Numerical study of the effects of thermal barrier coating and turbulence intensity on cooling performances of a nozzle guide vane. Energies, 2017, 10(3): 362.
[17] Vo D.-T., Mai T.D., Kim B., et al., Numerical study on the influence of coolant temperature, pressure, and thermal barrier coating thickness on heat transfer in high-pressure blades. International Journal of Heat and Mass Transfer, 2022, 189: 122715.
[18] Liu Z.Y., Zhu W., Yang L., et al., Numerical prediction of thermal insulation performance and stress distribution of thermal barrier coatings coated on a turbine vane. International Journal of Thermal Sciences, 2020, 158: 106552.
[19] Khor K.A., Gu Y.W., Thermal properties of plasma-sprayed functionally graded thermal barrier coatings. Thin Solid Films, 2000, 372(1–2): 104–113.
[20] Chen X., Li J., Long Y., et al., A conjugate heat transfer and thermal stress analysis of film-cooled superalloy with thermal barrier coating. ASME Turbo Expo 2020: Power for Land, Sea, and Air, Virtual, Online, 2020, Paper No. GT2020-16241.
[21] An K., Ravichandran K.S., Dutton R.E., et al., Microstructure, texture, and thermal conductivity of single-layer and multilayer thermal barrier coatings of Y2O3-stabilized ZrO2 and Al2O3 made by physical vapor deposition. Journal of the American Ceramic Society, 1999, 82(2): 399–406.
[22] Hahn D.W., Özisik M.N., Heat conduction, fourth edition, John Wiley & Sons, New York, 2012.
[23] Amiri D.A., Emamian A., Sajjadi H., et al., A comprehensive review on multi-dimensional heat conduction of multi-layer and composite structures: analytical solutions. Journal of Thermal Science, 2021, 30(6): 1875–1907.
[24] Hylton L., Mihelc M., Turner E., Analytical and experiment evaluation of the heat transfer distribution over the surface of turbine vane. NASACR-168015, 1985.
[25] Langtry R.B., Menter F.R., Correlation-based transition modeling for unstructured parallelized computational fluid dynamics codes. AIAA Journal, 2009, 47(12): 2894–2906.
[26] Langtry R.B., Menter F.R., Likki S.R., et al., A correlation-based transition model using local variables—part II: test cases and industrial applications. Journal of Turbomachinery, 2006, Paper No. TURBO-05-1023.
[27] Menter F.R., Langtry R.B., Likki S.R., et al., A correlation-based transition model using local variables—part I: model formulation. Journal of Turbomachinery, 2006, 128(3): 413–422.
[28] Krishna A.V., Parammasivam K., Thermal barrier coated surface modifications for gas turbine film cooling: a review. Journal of Thermal Analysis and Calorimetry, 2021, 146(2): 545–580.
[29] Davidson F.T., KistenMacher D.A., Bogard D.G., Film cooling with a thermal barrier coating: round holes, craters, and trenches. Journal of Turbomachinery, 2014, 136(4): 041007.
[30] Yang S.M., Tao W.Q., Heat Transfer, fourth edition, Higher Education Press, Beijing, 2006, pp. 54–54.
[31] Chi Z.R., Mechanism and optimization methods of gas turbine cooling structures. Tsinghua University, Beijing, China, 2014.
[32] Sinha A.K., Bogard D.G., Crawford M.E., Film-cooling effectiveness downstream of a single row of holes with variable density ratio. Journal of Turbomachinery, 1991, 113(3): 442–449.
[33] Han J.-C., Dutta S., Ekkad S., Gas turbine heat transfer and cooling technology, second ed., CRC press, Boca Raton, 2013.
[34] Lutum E., Johnson B.V., Influence of the hole length-to-diameter ratio on film cooling with cylindrical holes. Journal of Turbomachinery, 1999, 121(2): 209–216.
Options
Outlines

/

〈 〉

Wechat

Sponsored by: Institute of Engineering Thermophysics, Chinese Academy of Sciences　Publisher: Science Press

Copyright © 2023 Journal of Thermal Science