Volume 20, Issue 2 (February 2020)                   Modares Mechanical Engineering 2020, 20(2): 329-340 | Back to browse issues page

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Hosseini Baghdad Abadi S, zirak S, Rajabi Zargar Abadi M. Experimental and Numerical Investigation of Square Wave Pulsed Film Cooling Performance on a Flat Plate. Modares Mechanical Engineering 2020; 20 (2) :329-340
URL: http://mme.modares.ac.ir/article-15-29994-en.html
1- Energy Conversion Department, Mechanical Engineering Faculty, Semnan University, Semnan, Iran
2- Energy conversion Department, Mechanical Engineering Faculty, Semnan University, Semnan, Iran , s_zirak@semnan.ac.ir
Abstract:   (4655 Views)

In this research, the effect of square wave pulsating air on temperature distribution and film cooling effectiveness of flat plate at different frequencies and blowing ratios is experimentally and numerically investigated. Hot air is injected through the holes at an angle of 25 degrees. Square wave pulsed flow is generated at four frequencies of 2, 10, 50, 100 Hz, and five blowing ratios of 0.5, 1, 1.5, 2.4 and 3. To study the film cooling, Navier-Stokes equations are solved by a Reynolds average method. The SST k-ω model was used for turbulent modeling. The results showed that the film cooling effectiveness decreases with increasing of blowing ratio along with an increase in its rate of changes. The difference of centerline film cooling effectiveness between the numerical and experimental values decreases with increasing distance from the edge of injection hole. In general, pulsating decreases film cooling effectiveness in comparison with steady-state. The lift-off of the local jet increases under pulsation. In the pulsating state, the overall film cooling effectiveness decreases by increasing the blowing ratio at a constant frequency. On the other hand, increasing the frequency increases the overall efficiency of film cooling. The maximum averaged centerline effectiveness was obtained at a frequency of 100 Hz and a blowing ratio of 0.5 and the minimum value was obtained for a frequency of 2 Hz and a blowing ratio of 3. For pulsed flow, the maximum and minimum differences of the averaged centerline film cooling effectiveness between experimental and numerical results were 25.55% and 0.717%, respectively.

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Article Type: Original Research | Subject: Heat & Mass Transfer
Received: 2019/01/31 | Accepted: 2019/12/13 | Published: 2020/02/1

References
1. Han JC, Rallabandi AP. Turbine blade film cooling using PSP technique. Frontiers in Heat and Mass Transfer. 2010;1(1):013001. [Link] [DOI:10.5098/hmt.v1.1.3001]
2. Li GC, Yang P, Zhang W, Wu Z, Kou ZH. Enhanced film cooling performance of a row of cylindrical holes embedded in the saw tooth slot. International Journal of Heat and Mass Transfer. 2019;132:1137-1151. [Link] [DOI:10.1016/j.ijheatmasstransfer.2018.12.080]
3. Rutledge JL. Pulsed film cooling on a turbine blade leading edge [dissertation]. Ohio: Air Force Institute of Technology; 2009. [Link] [DOI:10.2514/6.2009-5103]
4. Qingzong X, Qiang D, Pei W, Junqiang Z. Computational study of film cooling and flowfields on a stepped vane endwall with a row of cylindrical hole and interrupted slot injections. International Journal of Heat and Mass Transfer. 2019;134:796-806. [Link] [DOI:10.1016/j.ijheatmasstransfer.2019.01.093]
5. Dano B, Liburdy J. Vortical structure of a 45 degree inclined pulsed jet in crossflow. Proceedings of the 36th AIAA Fluid Dynamics Conference and Exhibit; 2006, June 5-8; San Francisco. Reston: AIAA; 2006. [Link] [DOI:10.2514/6.2006-3543]
6. Rolls Royce P. The jet engine. 5th edition. New York: John Wiley and Sons; 2015. [Link]
7. Han C, Ren J, Jiang H. Experimental investigations of SYCEE film cooling performance on a plate and a tested vane of an F-class gas turbine. Proceedings of the ASME Turbo Expo: Turbine Technical Conference and Exposition. Volume 5b: Heat transfer; 2014, June 16-20; Dusseldorf, Germany. New York: American Society of Mechanical Engineers. [Link] [DOI:10.1115/GT2014-25774]
8. Wu H, Cheng H, Li Y, Rong C, Ding S. Effects of side hole position and blowing ratio on sister hole film cooling performance in a flat plate. Applied Thermal Engineering. 2016;93:718-730. [Link] [DOI:10.1016/j.applthermaleng.2015.09.118]
9. Zulkifli R, Sopian K, Abdullah S, Takriff MS. Effect of pulsating circular hot air jet frequencies on local and average nusselt number. American Journal of Engineering and Applied Sciences. 2008;1(1):57-61. [Link] [DOI:10.3844/ajeassp.2008.57.61]
10. Mayhew JE, Baughn JW, Byerley AR. The effect of freestream turbulence on film cooling adiabatic effectiveness. International Journal of Heat and Fluid Flow. 2003;24(5):669-679. [Link] [DOI:10.1016/S0142-727X(03)00081-X]
11. Seo HJ, Lee JS, Ligrani PM. The effect of injection hole length on film cooling with bulk flow pulsations. International Journal of Heat and Mass Transfer. 1998;41(22):3515-3528. [Link] [DOI:10.1016/S0017-9310(98)00042-8]
12. Ligrani PM, Gong R, Cuthrell JM, Lee JS. Bulk flow pulsations and film cooling-II. Flow structure and film effectiveness. International Journal of Heat and Mass Transfer. 1996;39(11):2283-2292. [Link] [DOI:10.1016/0017-9310(95)00287-1]
13. Jung IS, Lee JS, Ligrani PM. Effects of bulk flow pulsations on film cooling with compound angle holes: Heat transfer coefficient ratio and heat flux ratio. Journal of Turbomachinery. 2002;124(1):142-151. [Link] [DOI:10.1115/1.1400110]
14. El-Gabry LA, Rivir RB. Effect of pulsed film cooling on leading edge film effectiveness. Journal of Turbomachinery. 2012;134(4):041005. [Link] [DOI:10.1115/1.4003653]
15. Shahdad MH, Adami M, Mostoufi Zadeh AR. Numerical analysis of cooling of vanes of the first row of a turbine of a specific engine with film cooling and thermal shield coating and its numerical optimization. Proceedings of the 14th Conference of Iranian Aerospace Society; 2015, March 3-5; Tehran. Tehran: Scientific Information Database (SID); 2015. [Persian] [Link]
16. Akbari N, Pooladgar Y. Theoretical analysis of film cooling. Proceedings of the 14th Conference of Iranian Aerospace Society; 2015, March 3-5; Tehran. Tehran: Scientific Information Database (SID); 2015. [Persian] [Link]
17. Mahabadi Naderi H, Rajabi Zargarabadi M, Biglari M. Estimation of the turbulent Prandtl number in film cooling flow. Modares Mechanical Engineering. 2012;12(4):69-79.[Persian] [Link]
18. Stenger D, Ghia U, Ou S, Thornburg H. Numerical simulation of continuous and pulsed film cooling on a turbine-blade leading-edge model, including surface conductance. Proceedings of the 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition; 2010, June 4-7; Orlando, Florida. Reston: AIAA; 2010. [Link] [DOI:10.2514/6.2010-1474]
19. Hosseini Baghdad Abadi SM, Zirak S, Rajabi Zargar Abadi M. Numerical simulation of the sinusoidal wave pulsed film cooling effectiveness due to the changing cooling injection parameters. Modares Mechanical Engineering. 2019;19(1):191-200. [Persian] [Link]
20. Choi JU, Kim GM, Lee HC, Kwak JS. Optimization of the Coanda bump to improve the film cooling effectiveness of an inclined slot. International Journal of Thermal Sciences. 2019;139:376-386. [Link] [DOI:10.1016/j.ijthermalsci.2019.02.013]
21. Fraas M, Glasenapp T, Schulz A, Bauer HJ. Optimized inlet geometry of a laidback fan-shaped film cooling hole-Experimental study of film cooling performance. International Journal of Heat and Mass Transfer. 2019;128:980-990. [Link] [DOI:10.1016/j.ijheatmasstransfer.2018.09.035]
22. Coulthard SM, Volino RJ, Flack KA. Effect of jet pulsing on film cooling-part I: Effectiveness and flow-field temperature results. Journal of Turbomachinery. 2006;129(2):232-246. [Link] [DOI:10.1115/1.2437231]

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