پیوندهای مفید
آمار
| تعداد نشریات | 9 |
| تعداد شمارهها | 452 |
| تعداد مقالات | 5,750 |
| تعداد مشاهده مقاله | 8,245,871 |
| تعداد دریافت فایل اصل مقاله | 6,764,764 |
Optimization of cooling system of circular to rectangular transition duct in a turbine engine nozzle | ||
| AUT Journal of Mechanical Engineering | ||
| دوره 9، شماره 2، 2025، صفحه 123-142 اصل مقاله (1.85 M) | ||
| نوع مقاله: Research Article | ||
| شناسه دیجیتال (DOI): 10.22060/ajme.2025.23303.6120 | ||
| نویسندگان | ||
| Behrooz Shahriari* 1؛ Mojtaba Dehghani1؛ Parviz Hashemi1؛ Mojtaba Mohamad Hassanzade2 | ||
| 1Faculty of Mechanics, Malek Ashtar University of Technology, Isfahan, Iran | ||
| 2Faculty of Aerospace, Malek Ashtar University of Technology, Tehran, Iran | ||
| چکیده | ||
| This research focuses on optimizing the cooling system of a circular-to-rectangular transition duct in a turbine engine nozzle, a critical step in enhancing engine efficiency by enabling higher turbine inlet temperatures and increased thrust through afterburner usage, both of which significantly elevate exhaust gas temperatures. The study employs a combined film and impingement cooling method and utilizes fluent computational fluid dynamics software for analysis and optimization. Experimental design methodology was used to identify key parameters for optimizing the geometry for three blowing ratios (0.5, 1, and 1.5). Simulation results demonstrate that the optimal cooling configuration for all blowing ratios includes three rows of film cooling. The most influential parameters on cooling efficiency were found to be the diameter of the film cooling holes and the number of film cooling rows. For a blowing ratio of 1.5, increasing the hole diameter and the number of cooling rows resulted in a 32% and 33% increase in cooling efficiency, respectively. Regarding the relationship between cooling angle and efficiency, it was observed that efficiency increased up to 20 degrees and then decreased in blowing ratios of 0.5 and 1.5, while in a blowing ratio of 1, efficiency increased up to 30 degrees and then decreased. This research provides valuable insights into optimizing the cooling system of turbine engine nozzles, enabling more efficient and powerful engines. | ||
| کلیدواژهها | ||
| Air Turbine Engine؛ Rectangular Nozzle؛ Transition Duct؛ Combined Cooling؛ Cooling Efficiency | ||
| مراجع | ||
|
[1] J. Niu, C. Liu, H. Liu, X. Xiao, J. Lin, Theoretical and experimental analysis of overall cooling effectiveness for afterburner double-wall heat shield, International Journal of Heat and Mass Transfer, 176 (2021) 121360.
[2] Y. Jia, Y. Liu, Z. Meng, W. Yin, W. Hua, Numerical study on film cooling effectiveness from spiral-channel hole, International Communications in Heat and Mass Transfer, 143 (2023) 106716.
[3] R.D. Plant, J. Friedman, M.Z. Saghir, A review of jet impingement cooling, International Journal of Thermofluids, 17 (2023) 100312.
[4] D.E. Metzger, R.S. Bunker, Local heat transfer in internally cooled turbine airfoil leading edge regions: Part II-impingement cooling with film coolant extraction, (1990) 459-466.
[5] V.K. Garg, R.E. Gaugler, Effect of velocity and temperature distribution at the hole exit on film cooling of turbine blades, American Society of Mechanical Engineers, (1997) 343-351.
[6] D. Walters, J. Leylek, A systematic computational methodology applied to a three-dimensional film-cooling flowfield, (1997) 777-785.
[7] S. Baldauf, A. Schulz, S. Wittig, High-resolution measurements of local effectiveness by discrete hole film cooling, 123(4) (2001) 758-765.
[8] R. Kaszeta, T.W. Simon, Measurement of eddy diffusivity of momentum in film cooling flows with streamwise injection, J. Turbomach., 122(1) (2000) 178-183.
[9] F. Bazdidi-Tehrani, A.A. Mahmoodi, Investigation of the effect of turbulence intensity and injection angle on the flow and temperature field in the single hole film cooling technique, International Journal of Engineering Science, 4 (2002).
[10] S. Zecchi, L. Arcangeli, B. Facchini, D. Coutandin, Features of a cooling system simulation tool used in the industrial preliminary design stage, Turbo Expo: Power for Land, Sea, and Air, 41685 (2004) 493-501.
[11] J.E. Albert, D.G. Bogard, F. Cunha, Adiabatic and overall effectiveness for a film cooled blade, Turbo Expo: Power for Land, Sea, and Air, 41677 (2004) 251-259.
[12] M. Ghorab, S.I. Kim, I. Hassan, Conjugate heat transfer and film cooling of a multi-stage cooling scheme, ASME International Mechanical Engineering Congress and Exposition, 48715 (2008) 1249-1257.
[13] L.D. Dobrowolski, D.G. Bogard, J. Piggush, A. Kohli, Numerical simulation of a simulated film cooled turbine blade leading edge including conjugate heat transfer effects, ASME International Mechanical Engineering Congress and Exposition, 43826 (2009) 2145-2156.
[14] S. Ravelli, L. Dobrowolski, D.G. Bogard, Evaluating the effects of internal impingement cooling on a film cooled turbine blade leading edge, Turbo Expo: Power for Land, Sea, and Air, 43994 (2010) 1655-1665.
[15] B. Suresh, A. Brijesh, V. Kesavan, S.K. Kumar, Heat Transfer and Flow Studies of Different Cooling Configurations for Gas Turbine Rotor Blade, in: Gas Turbine India Conference, American Society of Mechanical Engineers, 49644 (2014), V001T004A006.
[16] S.R. Klavetter, J.W. McClintic, D.G. Bogard, J.E. Dees, G.M. Laskowski, R. Briggs, The effect of rib turbulators on film cooling effectiveness of round compound angle holes fed by an internal cross-flow, Journal of Turbomachinery, 138(12) (2016) 121006.
[17] J. Wang, B. Sunden, H. Wu, J. Yang, C. Gu, Q. Wang, Conjugated heat transfer analysis of a film cooling passage with turbulator ribs, Heat Transfer Research, 47(2) (2016).
[18] B. Zhao, M. Hu, X. Ao, N. Chen, G. Pei, Radiative cooling: A review of fundamentals, materials, applications, and prospects, Applied energy, 236 (2019) 489-513.
[19] A. Radchenko, E. Trushliakov, K. Kosowski, D. Mikielewicz, M. Radchenko, Innovative turbine intake air cooling systems and their rational designing, Energies, 13(23) (2020) 6201.
[20] T. Jackowski, M. Elfner, H.-J. Bauer, Experimental study of impingement Effusion-Cooled Double-Wall combustor liners: thermal analysis, Energies, 14(16) (2021) 4843.
[21] S. Fan, W. Li, Photonics and thermodynamics concepts in radiative cooling, Nature Photonics, 16(3) (2022) 182-190.
[22] J. Zhang, Q. Zheng, J. Xu, G. Yue, Y. Jiang, Conjugate heat transfer and flow analysis on double-wall cooling with impingement induced swirling and film cooling, Applied Thermal Engineering, 223 (2023) 120014.
[23] A. ANSYS FLUENT, Fluent Theory Guide, (2013). | ||
|
آمار تعداد مشاهده مقاله: 551 تعداد دریافت فایل اصل مقاله: 433 |
||