دانشگاه تربیت دبیر شهید رجائی

  اخبار و اعلانات

 آمار

تعداد نشریات13
تعداد شماره‌ها200
تعداد مقالات2,008
تعداد مشاهده مقاله2,680,173
تعداد دریافت فایل اصل مقاله1,937,363
Sahu, Mithilesh, Shaik, Moughbul. (1400). Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes. فناوری آموزش, 11(2), 397-407. doi: 10.22061/jcarme.2021.6418.1816
Mithilesh K Sahu; Moughbul Basha Shaik. "Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes". فناوری آموزش, 11, 2, 1400, 397-407. doi: 10.22061/jcarme.2021.6418.1816
Sahu, Mithilesh, Shaik, Moughbul. (1400). 'Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes', فناوری آموزش, 11(2), pp. 397-407. doi: 10.22061/jcarme.2021.6418.1816
Sahu, Mithilesh, Shaik, Moughbul. Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes. فناوری آموزش, 1400; 11(2): 397-407. doi: 10.22061/jcarme.2021.6418.1816

Numerical investigation on cooling performance of a twisted gas turbine blade with leading edge cooling holes

Journal of Computational & Applied Research in Mechanical Engineering (JCARME)
مقاله 9، دوره 11، شماره 2 - شماره پیاپی 22، خرداد 2022، صفحه 397-407    اصل مقاله (666.49 K)
نوع مقاله: Research Paper
شناسه دیجیتال (DOI): 10.22061/jcarme.2021.6418.1816
نویسندگان
Mithilesh K Sahu* ؛ Moughbul Basha Shaik
Department of Mechanical Engineering, Gayatri Vidya Parishad College of Engineering (Autonomous), Madhurawada, AP, 530048, India
تاریخ دریافت: 25 دی 1398،  تاریخ بازنگری: 24 خرداد 1400،  تاریخ پذیرش: 12 تیر 1400 
چکیده
The new and advance technologies for higher performance and lower maintenance are required to operate  gas turbines at higher operating temperatures. Higher turbine inlet temperature results in higher blade metal temperatures. These variations in temperatures of the blade material must be limited such that the blades have a sufficient life span. To make blade material temperature within the limits, the coolant air is bled from the compressor to protect the outer surface of the turbine blade from the hot gases. The purpose of this study  is to investigate the cooling performance of a blade with leading edge cooling holes. The numerical simulation approach using ANSYS Fluent has been considered. The analysis is performed by taking different hole geometries namely cylindrical (model 1) and tapered (model 2) on the leading edge of the turbine blade for different blowing ratios. The analysis also compares the cooling effectiveness of the blade for two different coolants namely air and nitrogen. The results show that for highest effectiveness hole (E3 hole), Model 1 and Model 2 comparison suggest that Model 1 has 1.2% more cooling effectiveness for air as coolant. For E3 hole, the comparison of Model 1 between two coolants show that film cooling effectiveness of the air gives 0.6% more film cooling effectiveness compared to nitrogen. The presented work helps researchers and blade manufacturers to select the correct hole geometry, coolant type, and determine the best blowing ratio to improve the film cooling efficiency of gas turbine blades with leading edge holes.
کلیدواژه‌ها
Blowing ratios؛ Coolant density؛ Cooling performance؛ Numerical Approach؛ Gas turbine blade, Hole geometry
مراجع
[1] D. L. Schmidt, B. Sen, and D. G. Bogard, “Film cooling with compound angle holes: adiabatic effectiveness”, J. Turbomach., Vol. 118, No. 8, pp. 807–813, (2016).

[2] N. H. K. Chowdhury, S. A. Qureshi, M. Zhang, and J. C. Han, “Influence of turbine blade leading edge shape on film cooling with cylindrical holes”, Int. J. Heat Mass Trans., Vol. 115, No. 1, pp. 895-908, (2017).

[3] N. Nandakumar and N. S. Moorthi, “Performance analysis of gas turbine blade cooling by CFD”, IJAMPE, Vol. 1, No. 4, pp. 3-9, (2015).

[4] S. Paregouda and T. Rao, “CFD simulation on gas turbine blade and effect of hole shape on leading edge film cooling effectiveness”, IJMER, Vol. 3, No. 4, pp. 2066-2072, (2013).

[5] H. Brahmaiah and M. Lava Kumar, “Heat transfer analysis of gas turbine blade through cooling holes”, IJCER, Vol. 4, No. 7, pp. 72-79, (2014).

[6] L. Zeng, P. Chen, X. Li, J. Ren, and H. Jiang, “Influence of simplifications of blade in gas turbine on film cooling performance”, Appl. Therm. Eng., Vol. 128, No. 1, pp. 877–886, (2018).

[7] H. wang Li, F. Han, Z. yu Zhou, Y. wen Ma, and Z. Tao, “Experimental investigations of the effects of the injection angle and blowing ratio on the leading-edge film cooling of a rotating twisted turbine blade”, Int. J. Heat Mass Trans., Vol. 127, No. 1, pp. 856-869, (2018).

[8] T. Bacci et al., “Experimental and CFD analysis of a highly-loaded gas turbine blade”, Energy Procedia, Vol. 126, No. 1, pp. 770-777, (2017).

[9] M. K. Sahu and Sanjay, “Investigation of the effect of air film blade cooling on thermoeconomics of gas turbine based power plant cycle”, Energy, Vol. 115, No. 1, pp. 1320-1330, (2016).

[10] M. K. Sahu and Sanjay, “Comparative exergoeconomic analysis of basic and reheat gas turbine with air film blade cooling”, Energy, Vol. 132, No. 1, pp. 160-170, (2017).

[11] M. K. Sahu and Sanjay,“Exergoeconomic investigation of power utility based on air film blade cooled gas turbine cycle”, Appl. Therm. Eng., Vol. 122, No. 1, pp. 738-746, (2017).  

[12] M. K. Sahu and Sanjay,“Thermo-economic investigation of power utilities: intercooled recuperated gas turbine cycle featuring cooled turbine blades”, Energy, Vol. 138, No. 1, pp. 490-499, (2017).

[13] M. K. Sahu and Sanjay, “Comparative exergoeconomics of power utilities: air-cooled gas turbine cycle and combined cycle configurations”, Energy, Vol. 139, No. 1, pp. 42-51, (2017).

[14] M. K. Sahu and Sanjay, “Thermo-economic investigation of basic and intercooled gas turbine based power utilities incorporating air-film blade cooling”, J Clean. Prod., Vol. 170, No. 1, pp. 842-856, (2018).

[15] M. K. Sahu, T. Choudhary, and Y. Sanjay, “Thermoeconomic investigation of different gas turbine cycle configurations for marine application”, SAE Technical Papers, Vol. 2016 Oct., No. 1, pp. 1-7, (2016).

[16] G. E. Andrews, M. L. Gupta, and M. C. Mcpadi, “Full coverage discrete hole film cooling: cooling effectiveness”, Int J Turbo Jet Eng, Vol. 2, No. 3, pp. 199–212, (1985).

[17] G. E. Andrews, A. A. Asere, M. L. Gupta, and M. C. Mkpadi, “Full coverage discrete hole film cooling: the influence of hole size”, Int J Turbo Jet Eng, Vol. 2, No. 3, pp. 213–225, (1985).

[18] G. E. Andrews and M. C. Mkpadi, “Full coverage discrete hole wall cooling: discharge coefficients”, J. Eng. Gas Turbines Power, Vol. 106, No. 1, pp. 183–192, (1984). 

[19] G. E. Andrews, A. A. Asere, M. C. Mkpadi, and A. Tirmahi, ‘Transpiration cooling contribution of film cooling to the overall cooling effectiveness”, Int J Turbo Jet Eng, Vol. 3, No. 2, pp. 245–256, (1986).

[20] S. Mendez and F. Nicoud, “An adiabatic homogeneous model for the flow around a multi-perforated plate”, AIAA J, Vol. 46, No. 10, pp. 2623–2633, (2008).

[21] A. K. Sinha, D. G. Bogard, and M. E. Crawford, “Film cooling effectiveness downstream of a single row of holes with varying density ratio, J. Turbomach., Vol. 113, No. 2, pp. 442–449, (1991).

[22] A. K. Sinha, D. G. Bogard, and M. E. Crawford, “Gas turbine film cooling: flowfield due to a second row of holes”, J. Turbomach., Vol. 113, No. 3, pp. 450–456, (1991).

[23] G. Laschet, “Homogenization of the fluid flow and heat transfer in transpiration cooled multi-layer plates”, J. Comput. Appl. Math., Vol 168, No. 2, pp. 277–288, (2004).

[24] G. Laschet, R. Krewinkel, P. Hul, and D. Bohn, “Conjugate analysis and effective thermal conductivities of effusion-cooled multilayer blade sections”, Int. J. Heat Mass Transfer, Vol. 57, No. 2, pp. 812–821, (2013).

[25] M. Sasaki, K. Takahara, T. Kumagai, and M. Hamano, “Film cooling effectiveness for injection from multirow holes”, J. Eng. Power, Vol. 101, No. 1, pp. 101–108, (1979).

[26] D. E. Metzger, D. I. Takeuchi, and P. A. Keunstler, “Effectiveness and heat transfer with full coverage film cooling”, J. Eng. Power, Vol. 95, No. 3, pp. 180–184, (1973).

[27] E. R. G. Eckert, “Analysis of film cooling and full-coverage film cooling of gas turbine blades”, J. Eng. Gas Turbines Power, Vol. 106, No. 1,  pp. 206–213, (1984).

[28] R. E. Mayle and F. J. Camarata, “Multihole cooling film effectiveness and heat transfer”, J. Heat Transfer, Vol. 97, No. 4, pp. 534–538, (1975).   

[29] S. Ekkad, D. Zapata and J.-C. Han, “Film effectiveness over a flat surface with air and co2 injection through compound angle holes using a transient liquid crystal image method,” J. Turbomach., Vol. 119, No. 3, pp. 587–593, (1997).

[30] A.B. Mehendale, J.C. Han and S. Ou, “Influence of high mainstream turbulence on leading edge heat transfer,” J. Heat Transfer, Vol. 113, No. 4, pp. 843-850, (1991). 

آمار
تعداد مشاهده مقاله: 890
تعداد دریافت فایل اصل مقاله: 489


سامانه مدیریت نشریات علمی. قدرت گرفته از سیناوب