پیوندهای مفید
آمار
| تعداد نشریات | 8 |
| تعداد شماره‌ها | 432 |
| تعداد مقالات | 5,611 |
| تعداد مشاهده مقاله | 7,330,572 |
| تعداد دریافت فایل اصل مقاله | 6,138,812 |
بررسی تأثیر مشخصه‌های هندسی بر جریان داخل کانال در شرایط جریان مافوق‌صوت غیرواکنشی با حضور حفره | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| مقاله 6، دوره 53، شماره 11، بهمن 1400، صفحه 5409-5428 اصل مقاله (2.83 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2021.19574.7062 | ||
| نویسندگان | ||
| وحیده دشتی رحمت آبادی1؛ محسن آقا سید میرزا بزرگ2؛ سعید خردمند* 3 | ||
| 1دانشجوی دکترا- دانشگاه مالک اشتر | ||
| 2عضو هیئت علمی دانشگاه مالک اشتر، دانشیار | ||
| 3دانشگاه صنعتی مالک اشتر*مکانیک | ||
| چکیده | ||
| در کار حاضر، به بررسی جریان داخل یک کانال دارای حفره به عنوان محفظه احتراق یک موتور اسکرمجت پرداخته شده است. تحلیل‌های انجام شده در این تحقیق در خصوص تأثیر مشخصه‌های هندسی وابسته به حفره نظیر L/D (طول به عمق حفره)، H/D ( ارتفاع کانال به عمق حفره) و عددهای ماخ متفاوت در محدوده مافوق‌صوت بر روی کیفیت جریان داخل کانال محفظه احتراق است. در جریان غیرواکنشی مورد بررسی در این مقاله، مشخصه گردش به عنوان مشخصه وابسته به اختلاط تحلیل شده است. در تحلیل عددی، از معادلات دو بعدی ناویر استوکس به منظور حل جریان پایا و روش چگالی مبنا استفاده شده و مدل اغتشاشی مورد استفاده، روش k-ɛ استاندارد بوده است. به منظور شبیه سازی عددی از نرم افزار انسیس فلوئنت نسخه 18/2 استفاده شده است. نتایج به دست آمده نشان می‌دهد که با افزایش نسبت L/D، افزایش عدد ماخ و وجود زاویه در دیواره عقبی حفره، میزان گردش در لایه‌مرزی و در نتیجه اختلاط افزایش می‌یابد. هندسه‌های دارای H/D بزرگ‌تر، عملکرد بهتری را نسبت به سایر هندسه‌های مورد بررسی در مورد میزان تولید گردش و کاهش افت فشار کل از خود نشان دادند. همچنین با وجود اینکه نسبت H/D برابر با 1، گردش بیشتری نسبت به حالات دیگر دارد اما به دلیل بقای شوک مایل در برخی شرایط و ایجاد افت فشار کل قابل توجه، استفاده از آن در همه ماخ‌های مافوق‌صوت مطمئن نخواهد بود. | ||
| کلیدواژه‌ها | ||
| جریان مافوق‌صوت؛ حفره؛ غیر واکنشی؛ زاویه دیواره عقبی حفره؛ نسبت H/D و L/D | ||
| عنوان مقاله [English] | ||
| Investigation of Geometric Characteristics on the Non-Reaction Supersonic Flow inside the Channel with the Presence of Cavities | ||
| نویسندگان [English] | ||
| Vahideh Dashti Rahmat Abadi1؛ Mohsen A.S. Mirzabozorg2؛ Saeed Kheradmand3 | ||
| 1PHD Student, Malek Ashtar Uni. | ||
| 2Aerospace Department, Associated Professor | ||
| 3Mech. Dept., MUT, Iran | ||
| چکیده [English] | ||
| In the present work, the flow inside a channel with a cavity is investigated as a Scramjet combustion chamber. For this aim, the parameters such as L/D (cavity length to cavity depth), H/D (channel height to cavity depth), and varied Mach numbers are studied in the supersonic flow to investigate the effect of geometric parameters on channel flow in non- reacting conditions. In this work, vorticity is used as a mixing parameter. Two-dimensional Navier-Stokes equations are used to solve the steady-state flow. The density based method and standard k-ε Model are employed for numerical simulation. The results show that vorticity of boundary layer and thus mixing in flow is increased with growing of L/D, Mach number and having sweep angle for the cavity. Geometries with larger H/D performed better than other geometries in terms of generating vorticity and reducing Total pressure loss. Although the H/D = 1 ratio has a higher recirculation than others, it will not be reliable for all supersonic flow because of its considerable total pressure loss and the survival of the oblique shock in some conditions. | ||
| کلیدواژه‌ها [English] | ||
| Supersonic flow, Cavity, Non- reaction, Aft angle of cavity, L/D and H/D ratio | ||
| مراجع | ||
|
[1] A. Ben Yakar, R.K. Hanson, Cavity Flame-Holders for Ignition and Flame Stabilization in Scramjets: An Overview, Journal of Propulsion and Power, 17(4) (2001) 869-877. [2] S. Jeyakumar, S.M. Assis, K. Jayaraman, effect of Axisymmetric aft wall angle cavity in supersonic flowfield, International Journal of Turbo and Jet Engines, 35(1) (2018) 29-34. [3] K.N. Jayachandran, N. Nithin, S. Dhinesh, A.M. Irfan, D.T. Murugan, Performance Analysis of Double Cavity Based Scramjet Combustion at Mach 2 using CFD, International Journal of Emerging Technology and Advanced Engineering, 4(3) (2014) 110-119. [4] M.R. Gruber, R.A. Baurle, T. Mathur, K.Y. Hsu, Fundamental studies of cavity-based flameholder concepts for supersonic combustors, Journal of Propulsion and Power, 17(1) (2001) 146-153. [5] V. Sridhar, S.L. Gai, H. Kleine, A Numerical Investigation of Supersonic Cavity Flow At Mach 2, in: 18th Australasian Fluid Mechanics Conference, Launceston, Australia, 2012. [6] K.M. Kim, S.W. Baek, C.Y. Han, Numerical study on supersonic combustion with cavity-based fuel injection, International Journal of Heat and Mass Transfer, 47 (2004) 271-286. [7] M. Dharavath, P. Manna, D. Chakraborty, Numerical Investigation of Hydrogen-fuelled Scramjet combustor with cavity Flame Holder, Defence Science Journal, 64(5) (2014) 417-425. [8] W. Huang, Z.g. Wang, M. Pourkashanian, L. Ma, D.B. Ingham, S.B. Luo, J. Liu, Hydrogen fuelled scramjet combustor—the impact of fuel injection, in: Fuel Injection, Sciyo, 2010. [9] S.B. Luo, W. Huang, J. Liu, Z.G. Wang, Drag force investigation of cavities with different geometric configurations in supersonic flow, Science China Technological Science, 54(5) (2011) 1345-1350. [10] W. Huang, Z.G. Wang, L. Yan, W.D. Liu, Numerical validation and parametric investigation on the cold flow field of a typical cavity-based scramjet combustor, Journal of Acta Astrnautica, 80(1) (2012) 132-140. [11] W. Huang, M. Pourkashanian, L. Ma, D.B. Ingham, S.B. Luo, Z.g. Wang, Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method, Aerospace Science and Technology, 21 (2012) 24-30. [12] P. Hashemi, M. Dahghan Manshadi, A. Mostofizadeh, Role of the vortical structures in combustion of jet in cross flow at inlet of supersonic nozzle, Aerospace propulsion, 1(2) (2014) 11-22 (in persian). [13] M. Zahedzadeh, F. Ommi, Numerical Study of Staged Transverse Injection of Sonic Jets into Supersonic Crossflows behind a Step, Journal of Modeling in Engineering, 17(56) (2019) 281-291 (in persian). [14] M. Lahijani, S. Emami Koopaei, Effect of the number of cavity flame-holders on combustion efficiency and pressure recovery factor in a supersonic combustion chamber, Fuel and Combustion, 13(1) (2020 ) 98-117 (in persian). [15] F. Xing, M.M. Zhao, S. Zhang, Simulations of a Cavity Based Two-Dimensional Scramjet Model, in: 18th Australasian Fluid Mechanics Conference, Launceston, Australia, 2012. [16] D. Zhang, Q. Wang, Numerical Simulation of Supersonic Combustor with Innovative Cavity, International Conference on Advances in Computational Modeling and Simulation, Procedia Engineering, 31 (2012) 708-712. [17] M.F. Khan, R. Yadav, Z.A. Quadri, S.F. Anwar, Numerical Study of the Cavity Geometry on Supersonic Combustion with Transverse Fuel Injection, in: Numerical study of cavity geometry on fluid Mechanics and Fluid power, 2017, pp. 1509-1518. [18] W.L. Lui, L. Zhu, Y.Y. Qi, J.R. Ge, F. Luo, H.R. Zou, M. Wei, T.C. Jen, Effects of injection pressure variation on mixing in a cold supersonic combustor with kerosene fuel, Acta Astronautica, 139 (2017) 67-76. [19] W. Yang, J. Fu, X. Ma, R. Xing, Numerical Study on Configuration of Scramjet Combustor, in: IOP Conf. Materials Science and Engineering, 2018. [20] Z. Cai, M. Sun, Z. Wang, X. Bai, Effect of cavity geometry on fuel transport and mixing processes inascramjet combustor, ournal of Aerospace Science and Technology, 80 (2018) 309-314. [21] L. Suneetha, P. Randive, K.M. Pandey, Numerical investigation on mixing behavior of fuels inreacting and non-reacting flow condition of a cavity-strut based scramjet combustor, International Journal of Hydrogen Energy, 44(31) (2019) 16718-16734. [22] S. Jeyakumar, S.M. Assis, K.N. Jayachandran, Experimental Study on the characteristics of axisymmetric cavity actuated supersonic flow, Journl of Aerospace Engineering,SAGE, 0(0) (2016) 1-8. [23] S. Jeyakumar, S.M. Assis, K. Jayaraman, Effect of Axisymmetric Aft Wall Angle Cavity in Supersonic Flow Field, International Journal of Turbo and Jet Engines, 35(1) (2016). [24] S. Etheridge, J.G. Lee, C. Carter, M. Hagenmaier, R. Milligan, Effect of flow distortion on fuel/air mixing and combustion in an upstream-fueled cavity flameholder for a supersonic combustor, Experimental Thermal and Fluid Science, 88 (2017) 461-471. [25] Z. Cai, J. Zhu, M. Sun, Z. Wang, Effect of cavity fueling schemes on the laser-induced plasma ignition process in a scramjet combustor, Aerospace Science and Technology, 78 (2018) 197–204. [26] Y. Wang, Z. Wang, M. Sun, H. Wang, Z. Cai, Effects of fueling distance on combustion stabilization modes in a cavity- based scramjet combustor, Acta Astronautica, 155 (2019) 23-32. [27] G. Choubey, K. Pandey, Effect of variation of inlet boundary conditions on the combustion flow-field of a typical double cavity scramjet combustor, International Journal of Hydrogen Energy, 43 (2018/03/01). [28] O. Chakraborty, D. Sharma, K.O. Reddy, K.M. Pandey, CFD Analysis of Cavity Based Combustion of Hydrogen at Mach Number 1.4, Current Trends in Technology and Sciences, 1(3) (2012). [29] D.C. Wilcox, Turbulence Modeling for CFD, DCW Industries, 2002. [30] L. Abu-Farah, O. Haidn, H.P. Kau, Numerical simulations of single and multi-staged injection of H2 in a supersonic scramjet combustor, Propulsion and Power Research, 3(4) (2014) 175-186. | ||
|
آمار تعداد مشاهده مقاله: 785 تعداد دریافت فایل اصل مقاله: 870 |
||