پیوندهای مفید
آمار
| تعداد نشریات | 8 |
| تعداد شماره‌ها | 419 |
| تعداد مقالات | 5,514 |
| تعداد مشاهده مقاله | 6,256,647 |
| تعداد دریافت فایل اصل مقاله | 5,424,295 |
Stall Margin Improvement and Increase Pressure Ratio in Transonic Axial Compressor Using Circumferential Groove Casing Treatment | ||
| AUT Journal of Mechanical Engineering | ||
| مقاله 1، دوره 4، شماره 1، خرداد 2020، صفحه 3-16 اصل مقاله (950.42 K) | ||
| نوع مقاله: Research Article | ||
| شناسه دیجیتال (DOI): 10.22060/ajme.2019.14840.5746 | ||
| نویسندگان | ||
| Alireza Jafar Gholi Beik* 1؛ Seyed Hosein Torabi2؛ Hassan Basirat Tabrizi3 | ||
| 1Energy exchange, Mech. Eng. Dept., Jundi Shapor University of Technology, Dezful, Iran | ||
| 2Aerospace. Eng. Dept., Khaje Nasir Toosi University of Technology, Tehran, Iran | ||
| 3Amirkabir University of Technology(Tehran Polytechnic)*mechanical engineering | ||
| چکیده | ||
| Maximum pressure ratio and aerodynamic blades loading are the most important factors in designing axial compressor restricted by minimum airflow. The present work aims to stall margin and total pressure ratio in transonic axial compressor using circumferential groove casing treatment (CGCT). In the first step, untreated compressor was simulated, compared, and agreed well with the experimental data. Then the treated rotor was simulated and results indicated that using CGCT improves the stall margin and increases the rotor pressure ratio. Stall margin was improved by 8% and the pressure ratio before stall condition and at the design point increased by 2.6% and 2.8 %, respectively. Additionally, it replaces normal shock with oblique shock near instability, causing less total pressure drop, moreover, the oblique shocks occurrence restricts separation zones and assists the rotor to perform far from instability. Furthermore, axial speed passing through rotor in a certain mass flow increases by 15 m/s, and then kinetic energy and stability increased. However, total efficiency of rotor reduces near 1%. In the last step, engine was analyzed with the aid of cycle analysis and leads to 62kW increase in shaft power as well as 1.87 g/kNs less fuel consumption due to 2.8% increase in the rotor pressure ratio. | ||
| کلیدواژه‌ها | ||
| Transonic axial compressor؛ circumferential groove casing treatment؛ stall margin؛ efficiency | ||
| مراجع | ||
|
[1] H.W.P. Emmons, C.E. Grant, H.P. , Compressor surge and stall propagation, Transaction of the ASME, 77 (1955) 455-469. [2] E.M. Greitzer, Surge and Rotating Stall in Axial Flow Compressors—Part I: Theoretical Compression System Model, Journal of Engineering for Power, 98(2) (1976) 190-198. [3] J.J. Adamczyk, M.L. Celestina, E.M. Greitzer, Closure to “Discussions of ‘The Role of Tip Clearance in High-Speed Fan Stall’” (1993, ASME J. Turbomach., 115, p. 39), Journal of Turbomachinery, 115(1) (1993) 39-39. [4] D.A. Hoying, C.S. Tan, H.D. Vo, E.M. Greitzer, Role of Blade Passage Flow Structurs in Axial Compressor Rotating Stall Inception, Journal of Turbomachinery, 121(4) (1999) 735-742. [5] I. Wilke, H.P. Kau, A Numerical Investigation of the Flow Mechanisms in a HPC Front Stage With Axial Slots, (36894) (2003) 465-477. [6] H.D. Vo, C.S. Tan, E.M. Greitzer, Criteria for Spike Initiated Rotating Stall, (47306) (2005) 155-165. [7] C. Hah, J.r. Bergner, H.-P. Schiffer, Short Length-Scale Rotating Stall Inception in a Transonic Axial Compressor: Criteria and Mechanisms, (4241X) (2006) 61-70. [8] R. Davis, J. Yao, Axial Compressor Rotor Flow Structure at Stall-Inception, in: 44th AIAA Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, 2006. [9] C. Hah, J.r. Bergner, H.-P. Schiffer, Rotating Instability in a Transonic Compressor Rotor, in: INTERNATIONAL SYMPOSIUM ON AIR BREATHING ENGINES, American Institute of Aeronautics and Astronautics, Beijing, China, 2007, pp. 152. [10] X. Lu, J. Zhu, C. Nie, W. Huang, The Stability-Limiting Flow Mechanisms in a Subsonic Axial-Flow Compressor and Its Passive Control With Casing Treatment, (43161) (2008) 33-43. [11] A. Shabbir, J.J. Adamczyk, Flow Mechanism for Stall Margin Improvement due to Circumferential Casing Grooves on Axial Compressors, Journal of Turbomachinery, 127(4) (2004) 708-717. [12] X. Lu, J. Zhu, W. Chu, Numerical and experimental investigation of stepped tip gap effects on a subsonic axial-flow compressor rotor, Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 219(8) (2005) 605-615. [13] I. Wilke, H.P. Kau, G. Brignole, Numerically Aided Design of a High-Efficient Casing Treatment for a Transonic Compressor, (47306) (2005) 353-364. [14] X. Lu, W. Chu, J. Zhu, Y. Wu, Mechanism of the Interaction Between Casing Treatment and Tip Leakage Flow in a Subsonic Axial Compressor, (4241X) (2006) 79-90. [15] X. Lu, W. Chu, J. Zhu, Y. Wu, Experimental and Numerical Investigation of a Subsonic Compressor With Bend Skewed Slot Casing Treatment, (4241X) (2006) 49-59. [16] X. Lu, W. Chu, J. Zhu, Z. Tong, Numerical and Experimental Investigations of Steady Micro-Tip Injection on a Subsonic Axial-Flow Compressor Rotor %J International Journal of Rotating Machinery, 2006 (2006) 11. [17] A.M.T. Ghila, A. Tourlidakis, Unsteady Simulations of Recess Casing Treatment in Axial Flow Fans, in: ASME Turbo Expo 2006: Power for Land, Sea, and Air, ASME, 2006. [18] R. Emmrich, H. Hönen, R. Niehuis, Time Resolved Investigations of an Axial Compressor With Casing Treatment: Part 1 — Experiment, (47950) (2007) 189-198. [19] M.W. Müller, H.-P. Schiffer, C. Hah, Effect of Circumferential Grooves on the Aerodynamic Performance of an Axial Single-Stage Transonic Compressor, (47950) (2007) 115-124. [20] H. Jian, W. Hu, Numerical Investigation of Inlet Distortion on an Axial Flow Compressor Rotor with Circumferential Groove Casing Treatment, Chinese Journal of Aeronautics, 21(6) (2008) 496-505. [21] X. Dong, X. Liu, D. Sun, X. Sun, Experimental investigation on SPS casing treatment with bias flow, Chinese Journal of Aeronautics, 27(6) (2014) 1352-1362. [22] R. Taghavi-Zenouz, S. Abbasi, Alleviation of spike stall in axial compressors utilizing grooved casing treatment, Chinese Journal of Aeronautics, 28(3) (2015) 649-658. [23] F. Li, J. Li, X. Dong, D. Sun, X. Sun, Influence of SPS casing treatment on axial flow compressor subjected to radial pressure distortion, Chinese Journal of Aeronautics, 30(2) (2017) 685-697. [24] X. Xue, T. Wang, T. Zhang, B. Yang, Mechanism of stall and surge in a centrifugal compressor with a variable vaned diffuser, Chinese Journal of Aeronautics, 31(6) (2018) 1222-1231. [25] S. Kim, K. Kim, C. Son, Three-dimensional unsteady simulation of a multistage axial compressor with labyrinth seals and its effects on overall performance and flow characteristics, Aerospace Science and Technology, 86 (2019) 683-693. [26] A.J. Crook, E.M. Greitzer, C.S. Tan, J.J. Adamczyk, Numerical Simulation of Compressor Endwall and Casing Treatment Flow Phenomena, Journal of Turbomachinery, 115(3) (1993) 501-512. [27] 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). [28] A. Boretti, Experimental and computational analysis of a transonic compressor rotor, in: Proc. Of 17th Australasian Fluid Mechanics Conference, 2010, pp. 473-476. [29] Ansys, ANSYS Workbench Inc, in, 2017. [30] CATIA, in, 1992-2008. [31] E.-S. F, Aircraft Propulsion And Gas Turbine Engines, CRC Press INC (2008). [32] O.H.V. Mattingly J. D., Elements of Propulsion: Gas Turbines and Rockets, second ed, AIAA Education Serie, (2006). [33] GasTurb, Fletcher Gas Turbine Performance, in, Blackwell Science Ltd, 1998. | ||
|
آمار تعداد مشاهده مقاله: 1,043 تعداد دریافت فایل اصل مقاله: 1,060 |
||