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بررسی عددی تاثیر محرک پلاسما بر کارآیی خنککاری لایهای سوراخ تزریق لایهگستر | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| مقاله 5، دوره 50، شماره 6، بهمن و اسفند 1397، صفحه 1213-1228 اصل مقاله (1.81 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2017.12242.5287 | ||
| نویسندگان | ||
| سامرا دولتی1؛ نیما امانی فرد1؛ حامد محدث دیلمی* 2 | ||
| 1گروه مهندسی مکانیک، دانشکده فنی، دانشگاه گیلان، رشت، ایران | ||
| 2گروه مهندسی مکانیک، دانشکده فنی و مهندسی شرق گیلان، دانشگاه گیلان، رودسر، ایران | ||
| چکیده | ||
| در مطالعه حاضر، تاثیر محرک پلاسما بر میدانهای جریان و دما در روش خنک کاری لایهای بر روی یک صفحه تخت از طریق سوراخ تزریق لایه گستر به صورت عددی مورد بررسی قرار گرفته است. جریان سه بعدی، آشفته، غیرقابل تراکم و پایدار درنظر گرفته شده و شبیه سازیهای عددی با استفاده از شبکه سازمان یافته و غیریکنواخت، با بکارگیری مدل آشفتگی ِکی - اِپسیلون رینولدز پایین انجام شده است. به منظور اعتبارسنجی، نتایج عددی حاضر با نتایج تجربی و عددی مقایسه شده که از تطابق مناسبی برخوردار میباشد. سپس تاثیر پارامترهای مختلف جریانی و الکتریکی در حضور پلاسما بررسی شده است. در ادامه، با زاویه تزریق، نسبت طول به قطر سوراخ تزریق و نسبت چگالی ثابت، بررسی در مقادیر مختلف نسبت دمش 0/5 ،0/25 و ،1ولتاژهای ورودی 16 ،0و 24 کیلوولت و سرعتهای مختلف ورودی 9 ،4/5و 45متر برثانیه انجام شده است. مطابق نتایج، سوراخ تزریق لایه گستر نسبت به استوانهای به دلیل گسترش جانبی اثرات بهتری بر خنک کاری لایهای میگذارد. تاثیر محرک پلاسما بر کارآیی خنک کاری لایهای در نسبت دمش و سرعتهای پایین، بیشتر و با افزایش ولتاژ اعمالی نیز زیاد میشود. بنابراین حالت بهینه جهت ارتقای راندمان خنک کاری، در شرایط ولتاژهای بالاتر و نسبت دمش و سرعتهای پایینتر میباشد. | ||
| کلیدواژهها | ||
| خنککاری لایهای؛ محرک پلاسما؛ سوراخ تزریق لایهگستر؛ بررسی عددی | ||
| عنوان مقاله [English] | ||
| Numerical Investigation of the Effect of Plasma Actuator on the Film Cooling Effectiveness By Fan-Shaped Hole | ||
| نویسندگان [English] | ||
| S. Dolati1؛ N. Amanifard1؛ H. Mohaddes Deylami2 | ||
| 1Faculty of Mechanical Engineering, Guilan University, Guilan, Iran | ||
| 2Faculty of Technology and Engineering, East of Guilan, Guilan University, Guilan, Iran | ||
| چکیده [English] | ||
| In the present study, the effects of plasma actuator on the flow and thermal fields of the film cooling through a single row of inclined fan-shaped hole over a flat plate model have been investigated. Numerical simulations have been conducted for analyzing incompressible, turbulent and steady fluid flow. Simulations were implemented using non uniform structured grid and Low- Re k-ε turbulence model. The present computed results have been compared with the numerical and experimental results and it can be seen that the gained film cooling effectiveness distributions on the flat plate agree very well with them. Then, at constant degree injection angle, length-to-diameter ratio and density ratio, investigation has been implemented, with different blowing ratios of 0.25, 0.5 and 1, applied voltages of 0, 16 and 24kV and different velocities of 4.5, 9 and 45m/s. Based on the results, fan-shaped injection hole creates better film cooling performance. And also, the effect of plasma actuator on film cooling effectiveness is better at lower blowing ratios and this improvement becomes more obvious at higher applied voltages. Also, its performance is better in low velocities. Finally, the best situation for improvement of effectiveness is in higher voltages, lower blowing ratios and low velocities. | ||
| کلیدواژهها [English] | ||
| Film cooling, Plasma actuator, Fan-shaped hole, Numerical investigation | ||
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| مراجع | ||
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[1] A.K. Sinha, D.G. Bogard, M.E. Crawford, Film-cooling effectiveness ownstream of a single row of holes with variable density ratio, Journal of Turbomachinery, ASME, 113(3) (1991) 442-449. [2] J.R. Pietrzyk, D.G. Bogard, M.E. Crawford, Hydrodynamic measurements of jets in crossflow for gas turbine film cooling applications, Journal of Turbomachinery, ASME, 111(2) (1989) 139-145. [3] D.K. Walters, J.H. Leylek, Impact of film-cooling jets on turbine aerodynamic Losses, Journal of Turbomachinery, ASME, 122(3) (2000) 537-545. [4] M. Naghashnejad, N. Amanifard, H.M. Deylami, A predictive model based on a 3-d computational approach for film cooling effectiveness over a flat plate using gmdh-type neural networks, Journal of Heat and mass transfer, 50(1) (2014) 139-149. [5] D.G. Hyams, J.H. Leylek, A detailed analysis of film cooling physics: part III—streamwise injection with shaped holes, Journal of Turbomachinary, 122(1) (2000) 122–132. [6] C. Saumweber, A. Schulz, , Effect of geometry variations on the cooling performance of fan-shaped cooling holes, Journal of Turbomachinary, 134(6) (2012). [7] C. Saumweber, A. Schulz, Comparison of the cooling performance of cylindrical and fan-shaped cooling holes with special emphasis on the effect of internal coolant crossflow, ASME Paper GT2008-51036, (2008). [8] K.D. Lee, K.Y. Kim, Shape optimization of a fanshaped hole to enhance film-cooling effectiveness, International Journal of Heat and Mass Transfer, 53(15–16) (2010) 2996–3005. [9] M.A.H. Abdelmohimen, Improving film cooling from compound angle holes by adding secondary holes branched out from the main holes, Journal of Heat Mass Transfer, 53(5) (2017) 1805-1815. [10] A.E. Bergles, Techniques to enhance heat transfer, in handbook of heat transfer, 3: 11.11-11.76 (1998). [11] T.C. Corke, M.L. Post, D.M. Orlov, Single dielectric barrier discharge plasma enhanced aerodynamics: physics, modeling and applications, Review Article: Journal of Propulsion and Power, 24(5) (2008) 935-945. [12] Y.B. Suzen, P.G. Huang , J.D. Jacob, D.E. Ashpis , Numerical simulation of plasma based flow control applications, 35th Fluid Dynamics Conference and Exhibit, Totonto, Ontario, (2005). [13] B. Jayaraman, Y. Cho, W. Shyy, Modeling of dielectric barrier discharge plasma actuator, 38th AIAA Plasma dynamics and Lasers Conference, Miami FL, AIAA 2007-4531, (2007). [14] B. Jayaraman, W. Shyy, Modeling of dielectric barrier discharge-induced fluid dynamics and heat transfer, Journal of Progress in Aerospace Sciences, 44(3) (2007) 139-191. [15] M. Malik, L. Weinstein, M. Hussani, Ion wind drag reduction, AIAA 21st Aerospace Sciences Meeting & Exhibit, Hampton, VA AIAA 1983-0231, (1983). [16] A. ShamsTaleghani, A. Shadaram, M. Mirzaei, Experimental investigation of geometric and electrical characteristics by measurements of the induced flow, Modares Mechanical Engineering, 12(5) (2012) 132-145 (In Persian). [17] A. Rafi, N. Amanifard, H.M. Deylami, F. Dolati, Numerical investigation of the plasma actuator effects on the flow field and heat transfer coefficient in a flat channel, Modares Mechanical Engineering, 15(6) (2015) 23-30, 2 (In Persian). [18] Ch.Ch. Wang, S. Roy, Active cooling of turbine blades using horse-shoe plasma actuator, 47th AIAA Aerospace Sciences Meeting and Exhibit, Orlando, Florida, (2009). [19] Ch.Ch. Wang, S. Roy, Physics based analysis of horseshoe plasma actuator for improving film cooling effectiveness”, 47th AIAA Aerospace Sciences Meeting and Exhibit, Orlando, Florida., (2010). [20] J.L. Yu, L.M. He, Y.F. Zhu, W. Ding, Y.Q. Wang, Numerical simulation of the effect of plasma aerodynamic actuation on improving film hole cooling performance, Journal of Heat Mass Transfer, 49(6) (2013) 897-906. [21] B.E. Launder, B.I. Sharma, Application of the energy-dissipation model of turbulence to the calculation of flow near a spinning disc, Letters in Heat and Mass Transfer, 1(2) (1974) 131-138. [22] S.M. Kim, K.D. Lee, K.Y. Kim, A comparative analysis of various shaped film-cooling holes, Journal of Heat Mass Transfer, 48(11) (2012) 1929-(1939). [23] P. Dai, F. Lin, Numerical study on film cooling effectiveness from shaped and crescent holes, Journal of Heat Mass Transfer, 47(2) (2011) 147-154. [24] J.R. Roth, D.M. Sherman, S. Wilkinson, Electrohydrodynamic Flow Control with a GlowDischarge Surface Plasma, AIAA Journal, 38(7) (2000) 1166-1172 [25] C.L. Enloe, T.E. McLaughlin, R.D. VanDyken, K.D. Kachner, E.J. Jumper, T.C. Corke, M. Post, O. Haddad, Mechanisms and responses of a single dielectric barrier plasma actuator: geometric effects, AIAA Journal, 42(3) (2004) 595-604. [26] Salmasi, A. Shadaram, M. Mirzaei, A. ShamsTaleghani, Numerical and experimental investigation on the effect of a plasma actuator on NLF0414 airfoils efficiency after the stall, Journal of Tarbiat Modarres, 12(6) (2013) 104-116 (In Persian). [27] Y.B. Suzen, P.G. Huang , D.E. Ashpis , Numerical simulations of flow separation control in low pressure turbines using plasma actuators, 45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada, (2007). [28] D.M. Orlov, Modelling and simulation of single dielectric barrier discharge plasma actuators, Doctor of Philosophy thesis, Aerospace and Mechanical Engineering, Notre Dame, Indiana, (2006). [29] J.D. Jacob, K. Ramakumar, R. Anthony, R.B. Rivir, Control of Laminar and Turbulent Shear Flows Using Plasma Actuators, Fourth International Symposium on Turbulence and Shear Flow Phenomena, TSFP-4, Williamsburg, VA, (2005). [30] D. Greenblatt, R. Lautman,Inboard/outboard plasma actuation on a vertical-axis wind turbine, Original Research Article, Renewable Energy, 83 (2015) 1147-1156. [31] J.G. Lim, S. Seo, J.M. Koo, Ch.S. Seok, J.B. Choi, M.K. Kim, Parametric study for optimal design of an air plasma sprayed thermal barrier coating system with respect to thermal stress, Original Research Article, Surface and Coatings Technology, In Press, Accepted Manuscript, Available online 7, 315 (2017) 105-111. | ||
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