نوع مقاله : علمی پژوهشی

نویسندگان

1 دانشجوی کارشناسی‌ارشد، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران

2 دانشیار، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران

3 استادیار، گروه مهندسی مکانیک، دانشگاه شهید مدنی آذربایجان، تبریز، ایران

چکیده

با توجه به اهمیت بسیار بالای توربین گازی در تولید برق و همچنین توسعه روزافزون آن، از جمله­ی مهم­ترین روش­ها برای افزایش کارایی پره­های توربین گازی، افزودن پوشش محافظ گرمایی به سطح خارجی آنهاست. این پوشش­ها اینکه باعث بهبود خنک­کاری پره توربین گازی می­شوند، ولی معایبی نیز دارند که از جمله­ معایب آنها زبر نمودن سطح پره­ها است که ناخواسته منجر به جدایش­های جریان سیال داغ اطراف توربین گازی می­گردند، لذا سطوح زبر پوشش­های محافظ گرمایی می­بایست به طور بهینه و هدف­دار مورد استفاده قرار گیرند. در این تحقیق، با استفاده از نرم افزار تجاری فلوئنت به بررسی و تحلیل این نوع پوشش­ها، برای یافتن مناسب­ترین حالت ممکن جهت استفاده از آن پرداخته شده است. تاثیر پارامترهای زبری سطح، ضخامت و جنس پوشش­های محافظ گرمایی مورد بررسی قرار گرفته و بهینه ترین حالت برای پارامترهای مذکور، به ترتیب 1/0 م م، 38/0 م م و 7/2 وات بر متردرکلوین بدست آمده‌است.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

The Effect of Thermal Barrier Coating on the Thermal Performance of a Gas Turbine Blade

نویسندگان [English]

  • Ali Hajizadeh 1
  • Mir Yoseph Hashemi 2
  • Ali ziaie Asl 3

1 M.Sc. Student, Mechanical Engineering Department-, Azerbaijan Shahid Madani University, Tabriz, Iran

2 Associate Professor, Department of Mechanical Engineering, Azerbaijan Shahid Madani University, Tabriz, Iran

3 Assistant Professor, Mechanical Engineering Department, Azerbaijan Shahid Madani University, Tabriz, Iran

چکیده [English]

Due to the very high importance of gas turbine in electricity production and also its increasing development in the electricity industry, one of the most important methods to increase the efficiency of gas turbine blades is to add thermal barrier coating to their outer surface. These coatings improve the cooling of gas turbine blades, but they also have disadvantages such as roughness of their surface cause to the separation of the hot fluid flow around the turbine blades. The rough surfaces of thermal barrier coatings should be used optimally and purposefully. In this research, using commercial software of Fluent, this type of coating has been investigated and analyzed in order to find the most optimal possible mode for its use. The influence of surface parameters such as roughness, thickness and material of thermal barrier coatings have been investigated. The most optimal state for the mentioned parameters are: 0.1 mm, 0.38 mm and 2.7 W/m.K respectively.

کلیدواژه‌ها [English]

  • Thermal Barrier Coating
  • Gas Turbine
  • Roughness
  • Numerical Simulations
[1] S. W. Hwang, D. H. Kim, J. K. Min, and J. H. Jeong, “CFD analysis of fin tube heat exchanger with a pair of delta winglet vortex generators,” Journal of Mechanical Science and Technology, vol. 26(9), pp. 2949-2958, 2012.
[2] M. Yataghene and J. Legrand, “A 3D-CFD model thermal analysis within a scraped surface heat exchanger,” Computers & Fluids, vol. 71(9), pp. 380-399, 2013.
[3] S. Aradag, U. Olgun, F. Aktürk and B. Başıbüyük, “CFD analysis of cooling of electronic equipment as an undergraduate design project,” Computer Applications in Engineering Education, vol. 20(1), pp. 103-113, 2012.
[4] Y. Q. Liu, P. X. Jiang, Y. B Xiong and Y. P. Wang, “Experimental and numerical investigation of transpiration cooling for sintered porous flat plates,” Applied Thermal Engineering, vol. 50(1), pp. 997-1007, 2013.
[5] I. F. Zidane, K. M. Saqr, G. Swadener, X. Ma and M. F. Shehadeh, “On the role of surface roughness in the aerodynamic performance and energy conversion of horizontal wind turbine blades: a review,” International journal of energy research, vol. 40 (15), pp. 20-77, 2016.
[6] M. Valdes, M. D. Duran and A. Rovira, “Thermoeconomic optimization of combined cycle gas turbine power plants using genetic algorithms,” Applied Thermal Engineering, vol. 23(17), pp. 2169-2182, 2003.
[7] N. P. Padture, M. Gell and E. H. Jordan, “Thermal barrier coatings for gas-turbine engine applications,” Science, vol. 296 (5566), pp. 280-284, 2002.
[8] D. R. Clarke, M. Oechsner and N. P.  Padture, “Thermal-barrier coatings for more efficient gas-turbine engines,” MRS bulletin, vol. 37(10), pp.  891-898, 2012.
[9] F. Hummel, M. Lotzerich, P. Cardamone and L. Fottner, “Surface roughness effects on turbine blade aerodynamics,” Journal of Turbomachinery, vol. 127(3), pp 453-461, July 2005.
[10] T. Bai, J. Liu, W. Zhang and Z. Zou, “Effect of surface roughness on the aerodynamic performance of turbine blade cascade,” Propulsion and Power Research, vol. 3(2), pp. 82-89, 2014.
[11] S. S. Talebi, A. Mesgarpoor Tousi, “Investigation of Compressor Blade Roughness Increment Effect on Micro Turbine Performance,” AUT Journal of Mechanical Engineering, Vol. 49(3), pp. 471-484, 2017.
[12] K. Mulleners, G. Philipp and H. Sebastian, “Impact of surface roughness on the turbulent wake flow of a turbine blade,” Journal of Aerodynamics, 2014, 10.1155/2014/458757.
[13] I. F. Zidane, K. M. Saqr, G. Swadener, X. Ma and M. F. Shehadeh, “On the role of surface roughness in the aerodynamic performance and energy conversion of horizontal wind turbine blades: a review,” International journal of energy research, vol. 40(15), pp. 2055-2077, 2016.
[14] D. Li, R. Li, C. Yang and X. Wang, “Effects of surface roughness on aerodynamic performance of a wind turbine airfoil,” 2010 Asia-Pacific Power and Energy Engineering Conference. IEEE, pp. 1-4, 2010.
[15] W. Wu and U. Piomelli, “Effects of surface roughness on a separating turbulent boundary layer,” Journal of Fluid Mechanics. vol. 8(41), pp. 552-580, 2018.
[16] F. Yang, Z. Cai, Y. Chen, S. Dong, C. Deng, S. Niu and S. Wen, “A robotic polishing trajectory planning method combining reverse engineering and finite element mesh technology for aero-engine turbine blade TBCs,” Journal of Thermal Spray Technology, vol. 31(7), pp. 2050-2067, 2022.
[17] F. N. Nourin and R. S. Amano, “Heat Transfer Augmentation with Multiple Jet Impingement Cooling on Dimpled Surface for Gas Turbine Blades,” Journal of Energy Resources Technology, vol. 145(2), p. 022101, 2023.
[18] A. Roy, M. Searle, S. Ramesh and D.  Straub, “Investigation of Gas Turbine Internal Cooling Using Supercritical CO2—Effect of Surface Roughness and Channel Aspect Ratio,” Journal of Engineering for Gas Turbines and Power, vol. 144(11), p. 111019, 2022.
[19] Z. Mehmood, A. Sarosh and O. A. A. Awan, “Recent Advancements in Thermal Barrier Coatings (TBC) for High-Temperature Gas Turbines,” 2023.
[20] P. Gosselin, A. DeChamplain, S. Kalla and D. Kretschmer, “Three-dimensional CFD analysis of a gas turbine combustor,” In 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit (p. 3466), 2000.
[21] D. Borello, D. Anielli, F. Rispoli, A. Salvagni and P. Venturini, “Unsteady CFD analysis of erosion mechanism in the coolant channels of a rotating gas turbine blade,” In ASME Turbo Expo (pp. 15-19), 2015.
[22] M. Kaewbumrung, W. Tangsopa, and J. Thongsri, “Investigation of the trailing edge modification effect on compressor blade aerodynamics using SST k-ω turbulence model,” Aerospace, 6(4), p. 48, 2019.
[23] T. Akatsu, T. Kato, Y. Shinoda and F. Wakai, “Thermal barrier coating made of porous zirconium oxide on a nickel-based single crystal superalloy formed by plasma electrolytic oxidation,” Surface and Coatings Technology, vol. 223, pp. 47-51, 2013.
[24] M. Elfert, “The Research on a Film Cooling on a Surface of a Hot Gas Blade,” DLRBericht IB325-19-86, Cologne, Germany, 1986. (in German)
[25] W. Wroblewski, “Numerical evaluation of the blade cooling for the supercritical steam turbine,” Applied Thermal Engineering, vol. 51, pp 953-962, 2013.