Theoretical and Natural Science

- The Open Access Proceedings Series for Conferences


Theoretical and Natural Science

Vol. 14, 30 November 2023


Open Access | Article

Effect of thermal barrier coating on the thermal characteristic of turbine blade and its geometric optimization

Huaqing You * 1
1 University of Florida

* Author to whom correspondence should be addressed.

Theoretical and Natural Science, Vol. 14, 62-77
Published 30 November 2023. © 2023 The Author(s). Published by EWA Publishing
This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
Citation Huaqing You. Effect of thermal barrier coating on the thermal characteristic of turbine blade and its geometric optimization. TNS (2023) Vol. 14: 62-77. DOI: 10.54254/2753-8818/14/20240880.

Abstract

Thermal barrier coatings (TBC) and cooling structures are critical factors influencing the performance of aviation turbine blades. In order to investigate the effects of TBC and different cooling structures on the operating temperature and thermal stress of turbine blades, this study establishes a three-dimensional fluid-thermal-solid coupling model for aviation turbine blades. Based on this model, the study analyzes the effect of TBC thicknesses and different design architectures on the blade thermal characters, including temperature distribution and thermal stress analysis. Stress analysis is also conducted on blades with the best heat dissipation performance. The results indicate that as the thickness of the TBC increases, the blade temperature gradually decreases. Cooling channels effectively reduce turbine blade temperatures. It is also found that a reasonable increase in film cooling holes can further reduce blade temperatures. The thermal stress on the blade gradually decreases along the blade height, with the high-stress regions primarily concentrated at the junction between the blade body and the margin plate. The maximum stress is observed at the trailing edge. The conclusions of this study can provide valuable guidance for the design of aviation turbine blades with better thermal performance.

Keywords

Turbine Rotor Blade, Thermal Barrier Coating, Fluid-Thermo-Structure Coupling, Architecture Design

References

1. Wang Z C, Analysis and Application of high-efficiency of cooling technology of the turbine blade in Aircraft Engine. Modern Manufacturing Technology and Equipment, 2020(06):171-172.

2. Sun J Z, Zuo H F, The analysis of the influence of the operating conditions to the creep life of commercial engine turbine blades. Mechanical engineering of China, 2020(06):171-172.

3. S. Rani, A.K. Agrawal, V. Rastogi, Failure analysis of a first stage IN738 gas turbine blade tip cracking in a thermal power plant, Case Stud, Eng. Fail. Anal. 8 (2017) 1–10.

4. María García-Martínez , Juan Carlos del Hoyo Gordillo, Mª Pilar Valles Gonz´ alez, Failure study of an aircraft engine high pressure turbine (HPT) first stage blade, National Institute for Aerospace Technology, Spain, Engineering Failure Analysis 149 (2023) 107251

5. R. Wang, B. Zhang, D. Hu, K. Jiang, H. Liu, J. Mao, F. Jing, X. Hao, Thermomechanical fatigue experiment and failure analysis on a nickel-based superalloy turbine blade, Eng Fail Anal. 102 (2019) 35–45.

6. L.K. Bhagi, P. Gupta. A Brief Review on Failure of Turbine Blades, in: Proceedings STME-2013 Smart Technologies for Mechanical Engineering. 25-26, at Delhi Technological University, Delhi, Oct 2013.

7. Huang Y B. Development of Rapid Design Simulation System for Fluid-structure coupling Analysis of Aero-engine Turbine Cooling Blades, Master Thesis, 1-114, 2022

8. Di Carlo J A, Yun H M, Morscher G N, et al. Progressing SiC/SiC ceramic composite development for gas turbine hot section components under NASA EPM and UEET programs. Am Soc Mechan Eng, 2002, 4:39

9. Wang X G, Liu J L, Jin T et al. Tensile behaviors and deformation mechanisms of a nickel-base single crystal superalloy at different temperatures. Mater Sci Eng A, 2014,598:154

10. Bai X F, Zhao Q Y, Zeng W D, et al. Characteraization of hot deformation behavior of a biomedical titanium alloy TLM. Mater Sci Eng A,2014,598:236

11. Kuo C M, Yang Y T, Bor H Y, et al. Aging effects on the microstructure and creep behavior of Inconel 718 superalloy. Mater Sci Eng A, 2009,510-511:289

12. Huang H. Analysis of High and Low Cycle Stress Responses of Turbine Blades under the High Pressure in the Aero-engine, Master Thesis, 1-88, 2022

13. Peng B. Isogeometric analysis of fluid-structure interaction and shape optimal design of turbine blade, Master Thesis, 1-76, 2021

14. Z.Y. Liu, b, W. Zhu. 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.

15. Yang J, Zhang Z, Liu Z C. Thermal Fluid Structure Coupling Analysis Based on an Aeroengine Turbine Blade. Machinery, 2022(10):74-80

16. Zhang Z X, Zeng W, Bian X D, Gao G L, Xiao B. Effects of Thermal Barrier Coating on Temperature and Stress of Turbine Rotor Blade. Journal of Propulsion Technology, 2023(5)

17. Liu H S, Ma H, Parameterization of Modeling the Aero-turbine Blade Based on CATIA. Ordnance Industry Automation, 2015(04):56-60

18. Tang W Z, The numerical simulation of stress field in a turbine blade with TBCs based on fluid-solid coupling method, Master Thesis, 1-63, 2015

19. Academic Committee of the Superalloys, CSM. China Superalloy Handbook (first edition), Cast Superalloys. Beijing: China Quality Inspection Press, 2012

20. 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.

21. Siegel R, Spuckler C M. Analysis of Thermal Radiation Effects on Temperatures in Turbine Engine Thermal Barrier Coatings. Materials Science and Engineering A, 1998, 245 (2): 150-159.

Data Availability

The datasets used and/or analyzed during the current study will be available from the authors upon reasonable request.

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Volume Title
Proceedings of the 3rd International Conference on Computing Innovation and Applied Physics
ISBN (Print)
978-1-83558-191-9
ISBN (Online)
978-1-83558-192-6
Published Date
30 November 2023
Series
Theoretical and Natural Science
ISSN (Print)
2753-8818
ISSN (Online)
2753-8826
DOI
10.54254/2753-8818/14/20240880
Copyright
30 November 2023
Open Access
This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited

Copyright © 2023 EWA Publishing. Unless Otherwise Stated