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Investigating the Effect of Casing Injection Parameters on Transonic Axial Compressor Performance | ||
| AUT Journal of Mechanical Engineering | ||
| مقاله 4، دوره 7، شماره 4، 2023، صفحه 367-388 اصل مقاله (2.29 M) | ||
| نوع مقاله: Research Article | ||
| شناسه دیجیتال (DOI): 10.22060/ajme.2024.22716.6071 | ||
| نویسندگان | ||
| Sarallah Abbasi* 1؛ Mohammad Raiszadeh Oskoui2 | ||
| 1Department of Mechanical Engineering, Arak University of Technology, Arak, Iran, | ||
| 2Department of Mechanical Engineering, Sharif University of Technology, Tehran, Iran, | ||
| چکیده | ||
| One of the factors that can cause a reduction in the efficiency and performance of axial compressors is the tip leakage flow of the compressor blade. In the first, the compressor's performance curve is compared with experimental results obtained under the condition of no air injection, and a statistically significant agreement is observed. The present study investigates the impact of various parameters, including flow rate, diameter, angle, and injection location, on the compressor's performance curve and flow structure, taking into account the injection of air into a passage. The results indicate that the compressor's stall margin and stable range extension are at their maximum values at a specific scale of each of the aforementioned parameters. Any deviation from this scale, either by reducing or increasing the injection parameters, leads to a reduction in the above characteristics. Although the presence of injection leads to an increase in the total pressure ratio in all injection states compared to the state without injection, the adiabatic efficiency at similar mass flow rates exhibits no significant change. The results also indicate that flow injection in the most suitable state increases the stall margin amount by 27% and the stable range extension of the compressor by 192. | ||
| کلیدواژه‌ها | ||
| Axial Compressor؛ Numerical Simulation؛ Air Injection؛ Tip Leakage Flow؛ Stall | ||
| مراجع | ||
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[1] K. Yamada, H. Kikuta, K.-i. Iwakiri, M. Furukawa, S. Gunjishima, An Explanation for Flow Features of Spike-Type Stall Inception in an Axial Compressor Rotor, in: ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, 2012, pp. 2663-2675.
[2] C.-T. Dinh, M.-W. Heo, K.-Y. Kim, Aerodynamic performance of transonic axial compressor with a casing groove combined with blade tip injection and ejection, Aerospace Science and Technology, 46 (2015) 176-187.
[3] R.D. Moore, Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26 respectively, and with design pressure ratio of 2.05, National Aeronautics and Space Administration, 1980.
[4] S. Abbasi, A. Pirnia, R. Taghavi-Zenouz, Investigation of inlet distortion effects on axial compressor performance based on streamline curvature method, Journal of Theoretical and Applied Mechanics, 56(4) (2018) 1005-1015.
[5] S. Abbasi, A. Joodaki, Effect of blade profile on the performance characteristics of axial compressor in design condition, Journal of Computational & Applied Research in Mechanical Engineering (JCARME), 9(2) (2020) 287-296.
[6] S. Abbasi, A. Gholamalipour, Parametric study of injection from the casing in an axial turbine, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 234(5) (2020) 582-593.
[7] C. Hah, Effects of double-leakage tip clearance flow on the performance of a compressor stage with a large rotor tip gap, Journal of Turbomachinery, 139(6) (2017) 061006.
[8] X. Ren, C. Gu, A numerical study on the tip clearance in an axial transonic compressor rotor, Applied Thermal Engineering, 103 (2016) 282-290.
[9] D. Wisler, Loss reduction in axial-flow compressors through low-speed model testing, in, Citeseer, 1984.
[10] M.W. Wiseman, T.-H. Guo, An investigation of life extending control techniques for gas turbine engines, in: Proceedings of the 2001 American Control Conference.(Cat. No. 01CH37148), IEEE, 2001, pp. 3706-3707.
[11] I. Wilke, H.-P. Kau, G. Brignole, Numerically aided design of a high-efficient casing treatment for a transonic compressor, in: Turbo Expo: Power for Land, Sea, and Air, 2005, pp. 353-364.
[12] R. Davis, J. Yao, Axial compressor rotor flow structure at stall-inception, in: 44th AIAA Aerospace Sciences Meeting and Exhibit, 2006, pp. 419.
[13] M. Zhang, A. Hou, Investigation on stall inception of axial compressor under inlet rotating distortion, Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 231(10) (2017) 1859-1870.
[14] J.J. Adamczyk, M. Celestina, E. Greitzer, The role of tip clearance in high-speed fan stall, (1993).
[15] I. Wilke, H.-P. Kau, A numerical investigation of the flow mechanisms in a HPC front stage with axial slots, in: Turbo Expo: Power for Land, Sea, and Air, 2003, pp. 465-477.
[16] M. Howard, S. Gallimore, Viscous throughflow modeling for multistage compressor design, (1993).
[17] C. LeJambre, R. Zacharias, B. Biederman, A. Gleixner, C. Yetka, 1995 ASME Gas Turbine Award Paper: Development and Application of a Multistage Navier–Stokes Flow Solver: Part II—Application to a High-Pressure Compressor Design, (1998).
[18] M. Banjac, M.V. Petrovic, A. Wiedermann, Secondary flows, endwall effects, and stall detection in axial compressor design, Journal of Turbomachinery, 137(5) (2015) 051004.
[19] A. Sadagopan, C. Camci, A design strategy for a 6: 1 supersonic mixed-flow compressor stage, Aerospace Science and Technology, 87 (2019) 265-277.
[20] J. Luo, Design optimization of the last stage of a 4.5-stage compressor using a POD-based hybrid model, Aerospace Science and Technology, 76 (2018) 303-314.
[21] N. Tahara, M. Kurosaki, Y. Ohta, E. Outa, T. Nakakita, Y. Tsurumi, Early stall warning technique for axial flow compressors, in: Turbo Expo: Power for Land, Sea, and Air, 2004, pp. 375-384.
[22] M. Dhingra, Y. Neumeier, J. Prasad, A. Breeze-Stringfellow, H.-W. Shin, P.N. Szucs, A stochastic model for a compressor stability measure, in: Turbo Expo: Power for Land, Sea, and Air, 2006, pp. 833-843.
[23] Y. Liu, M. Dhingra, J. Prasad, Correlation measure-based stall margin estimation for a single-stage axial compressor, (2012).
[24] A. Young, I. Day, G. Pullan, Stall warning by blade pressure signature analysis, Journal of Turbomachinery, 135(1) (2013) 011033.
[25] F. Li, J. Li, X. Dong, Y. Zhou, D. Sun, X. Sun, Stall-warning approach based on aeroacoustic principle, Journal of Propulsion and Power, 32(6) (2016) 1353-1364.
[26] M.D. Hathaway, Passive endwall treatments for enhancing stability, 2007.
[27] S. Xiaofeng, D. Xu, S. Dakun, Recent development of casing treatments for aero-engine compressors, Chinese Journal of Aeronautics, 32(1) (2019) 1-36.
[28] J. Li, J. Du, C. Nie, H. Zhang, Review of tip air injection to improve stall margin in axial compressors, Progress in aerospace sciences, 106 (2019) 15-31.
[29] H. Chen, X. Huang, K. Shi, S. Fu, M. Ross, M.A. Bennington, J.D. Cameron, S.C. Morris, S. McNulty, A. Wadia, A computational fluid dynamics study of circumferential groove casing treatment in a transonic axial compressor, Journal of Turbomachinery, 136(3) (2014) 031003.
[30] T.-D. Vuong, K.-Y. Kim, C.-T. Dinh, Recirculation-groove coupled casing treatment for a transonic axial compressor, Aerospace Science and Technology, 111 (2021) 106556.
[31] J. Li, J. Du, F. Li, Q. Zhang, H. Zhang, Stability enhancement using a new hybrid casing treatment in an axial flow compressor, Aerospace science and technology, 85 (2019) 305-319.
[32] A. Epstein, J.F. Williams, E. Greitzer, Active suppression of aerodynamic instabilities in turbomachines, Journal of Propulsion and Power, 5(2) (1989) 204-211.
[33] C. Koch, L. Smith Jr, Experimental evaluation of outer case blowing or bleeding of single stage axial flow compressor. Part 4-Performance of bleed insert conFig.uration no. 3, 1968.
[34] C. Koch, L. Smith Jr, Experimental evaluation of outer casing blowing or bleeding of single stage axial flow compressor. Part 2-Performance of plain casing insert conFig.uration with undistorted inlet flow and boundary layer trip, 1968.
[35] C. Nie, Z. Tong, S. Geng, J. Zhu, W. Huang, Experimental investigations of micro air injection to control rotating stall, Journal of Thermal Science, 16 (2007) 1-6.
[36] H. Khaleghi, Effect of discrete endwall recirculation on the stability of a high-speed compressor rotor, Aerospace Science and Technology, 37 (2014) 130-137.
[37] X. Liu, J. Teng, J. Yang, X. Sun, D. Sun, C. He, J. Du, Calculation of stall margin enhancement with micro-tip injection in an axial compressor, Journal of Fluids Engineering, 141(8) (2019) 081109.
[38] J. Li, Self-adaptive stability-enhancing technology with tip air injection in an axial flow compressor, Journal of Turbomachinery, 139(1) (2017) 011008.
[39] I.B.Y. Ce, Steady air injection flow control parameters in a transonic axial compressor, Research Journal of Applied Sciences, Engineering and Technology, 5(4) (2013) 1441-1448.
[40] J. Li, J. Du, Z. Li, F. Lin, Stability enhancement with self-recirculating injection in axial flow compressor, Journal of Turbomachinery, 140(7) (2018) 071001.
[41] W. Wei, C. Wuli, H. Zhang, H. Kuang, Experimental and numerical study of tip injection in a subsonic axial flow compressor, Chinese Journal of Aeronautics, 30(3) (2017) 907-917.
[42] B. Beheshti, B. Farhanieh, K. Ghorbanian, J. Teixeira, P. Ivey, Performance enhancement in transonic axial compressors using blade tip injection coupled with casing treatment, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 219(5) (2005) 321-331.
[43] B.H. Beheshti, K. Ghorbanian, B. Farhanieh, J.A. Teixeira, P.C. Ivey, A new design for tip injection in transonic axial compressors, in: Turbo Expo: Power for land, sea, and air, 2006, pp. 39-47.
[44] A. Mushtaq, K. Parvez, S. Ahmad, J. Khan, Parametric study of tip injection on stability of transonic axial flow compressor, in: 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, 2011, pp. 744.
[45] L. Reid, R.D. Moore, Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor, 1978.
[46] G. Cassina, B.H. Beheshti, A. Kammerer, R.S. Abhari, Parametric study of tip injection in an axial flow compressor stage, in: Turbo Expo: Power for Land, Sea, and Air, 2007, pp. 137-145.
[47] J. Li, F. Lin, Z. Tong, C. Nie, J. Chen, The dual mechanisms and implementations of stability enhancement with discrete tip injection in axial flow compressors, Journal of Turbomachinery, 137(3) (2015) 031010.
[48] M.D. Hathaway, Self-recirculating casing treatment concept for enhanced compressor performance, 2002. | ||
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