پیوندهای مفید
آمار
| تعداد نشریات | 9 |
| تعداد شمارهها | 448 |
| تعداد مقالات | 5,737 |
| تعداد مشاهده مقاله | 8,060,397 |
| تعداد دریافت فایل اصل مقاله | 6,560,738 |
مطالعه عددی اثرات فاصله نوک پره بر عملکرد یک کمپرسور محوری چند مرحلهای گذرصوتی | ||
| نشریه مهندسی مکانیک امیرکبیر | ||
| دوره 57، شماره 2، 1404، صفحه 187-214 اصل مقاله (3.15 M) | ||
| نوع مقاله: مقاله پژوهشی | ||
| شناسه دیجیتال (DOI): 10.22060/mej.2025.23795.7821 | ||
| نویسندگان | ||
| علی حسن زاده بافقی؛ محمد جواد شهریاری؛ حسین خالقی* | ||
| دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران | ||
| چکیده | ||
| کمپرسورها که به منظور افزایش فشار گاز مورد استفاده قرار میگیرند در صنعت از اهمیت فراوانی برخوردار بوده و ممکن است به عنوان بخشی از یک ماشین بزرگتر مانند توربین گاز و یا به عنوان یک ماشین مجزا در واحدهای فرآیندی مورد استفاده قرار گیرند. با توجه به کاربرد فراوان کمپرسورها، بهبود عملکرد و افزایش بازه عملکردی آنها اهمیت فراوانی دارد و مطالعات زیادی در این زمینه و عوامل موثر بر آن انجام شده است. در این مطالعه، اثر فاصله نوک پره از پوسته بر عملکرد یک کمپرسور چند طبقه گذرصوتی با استفاده از شبیهسازی عددی مورد بررسی قرار گرفته است. ابتدا یک کمپرسور مبنای ناسا با دادههای موجود شبیهسازی و صحتسنجی شد. همچنین یک بررسی و صحتسنجی از طریق شبیهسازی تک طبقه هر یک از طبقات کمپرسور و مقایسه آن با نتایج شبیهسازی چند طبقه انجام شده است. سپس تأثیر افزایش لقی روتورها به 1/5 و 2 برابر حالت مبنا، در سه حالت مختلف (افزایش لقی در همه روتورها، تنها روتور اول یا تنها روتور دوم) بررسی گردیده است. نتایج نشاندهنده آن است که از بین این دو روتور، روتور با لقی بیشتر همان روتور عامل ناپایداری است و همچنین بازه عملکردی کمپرسور در مقایسه با شرایطی که لقی همه روتورها به یک اندازه افزایش یابد تقریبا مشابه است. | ||
| کلیدواژهها | ||
| کمپرسور چند طبقه؛ گذرصوتی؛ شبیهسازی عددی؛ لقی؛ ناپایداری؛ بازه عملکردی | ||
| عنوان مقاله [English] | ||
| A Numerical Study of the Effects of Blade Tip Clearance on the Performance of a Multi-Stage Transonic Axial Compressor | ||
| نویسندگان [English] | ||
| Ali Hassanzadeh Bafghi؛ Mohammad Javad Shahriyari؛ Hosein Khaleghi | ||
| Department of Aerospace Engineering, Amirkabir University of Technology, Tehran 15875-4413, Iran | ||
| چکیده [English] | ||
| Compressors are integral components in various industrial systems, ranging from standalone units in process plants to essential parts of gas turbines. Given the widespread application of compressors, improving their performance and expanding their operating range are of great importance, leading to extensive studies on this subject and the factors affecting it. In this study, the effect of blade tip clearance on the performance of a transonic multistage compressor was investigated using numerical simulation. First, a baseline NASA compressor was simulated and validated using available data. Additionally, a single-stage simulation of each compressor stage was conducted and validated by comparison with the multi-stage simulation results. Subsequently, the impact of increasing rotor clearances to 1.5 and 2 times the baseline level was examined in three different scenarios: increasing clearance for all rotors, only the first rotor, or only the second rotor. The results indicate that among these two rotors, the one with the larger clearance is the primary source of instability. Furthermore, the operating range of the compressor remains almost unchanged compared to the scenario where the clearance of all rotors is increased uniformly. | ||
| کلیدواژهها [English] | ||
| Multistage Compressor, Transonic, Numerical Simulation, Clearance, Instability, Operating Range | ||
| مراجع | ||
|
[1] M. Yadegari, A. Bak Khoshnevis, Numerical study of the effects of adverse pressure gradient parameter, turning angle and curvature ratio on turbulent flow in 3D turning curved rectangular diffusers using entropy generation analysis, The European Physical Journal Plus, 135(7) (2020) 1-21. [2] M. Yadegari, A. Bak Khoshnevis, Investigation of entropy generation, efficiency, static and ideal pressure recovery coefficient in curved annular diffusers, The European Physical Journal Plus, 136 (2021) 1-19. [3] M. Yadegari, A.B. Khoshnevis, Entropy generation analysis of turbulent boundary layer flow in different curved diffusers in air-conditioning systems, The European Physical Journal Plus, 135(6) (2020) 534. [4] H. Khaleghi, M.J. Shahriyari, M. Heinrich, A theory for predicting stall cell transient behavior, Amirkabir Journal of Mechanical Engineering, 53(9) (2021) 4773-4788. [5] H. Khaleghi, M.J. Shahriyari, M. Heinrich, A theory for rotating stall in contra-rotating fans, Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science, 235(18) (2021) 3764-3773. [6] M. Shahriyari, A. Firouzabadi, H. Khaleghi, S. Esmailifar, A new model for compressor surge and stall control, Scientific Reports, 14(1) (2024) 5347. [7] M. Shahriyari, H. Khaleghi, M. Heinrich, A model for predicting post-stall behavior of axial compressors, Journal of Applied Fluid Mechanics, 14(3) (2020) 897-908. [8] M.J. Shahriyari, H. Khaleghi, M. Heinrich, A model for stall and surge in low-speed contra-rotating fans, Journal of Engineering for Gas Turbines and Power, 141(8) (2019) 081009. [9] I. Day, E.M. Greitzer, N. Cumpsty, Prediction of compressor performance in rotating stall, J. Eng. Gas Turbines Power, 100(1) (1978) 1-12. [10] C. Koch, Stalling pressure rise capability of axial flow compressor stages, J. Eng. Gas Turbines Power, 103(4) (1981) 645-656. [11] R.E. Peacock, A review of turbomachinery tip gap effects: Part 1: Cascades, International Journal of Heat and Fluid Flow, 3(4) (1982) 185-193. [12] S. Puterbaugh, M. Brendel, Tip clearance flow-shock interaction in a transonic compressor rotor, Journal of propulsion and power, 13(1) (1997) 24-30. [13] H.D. Vo, Role of Tip Clearance Flow on Axial Compressor, Massachusetts Institute of Technology: Cambridge, MA, USA, 2002. [14] Z. Zhang, X. Yu, B. Liu, Characteristics of the tip leakage vortex in a low-speed axial compressor with different rotor tip gaps, in: Turbo Expo: Power for Land, Sea, and Air, American Society of Mechanical Engineers, 2012, pp. 311-322. [15] M.P. Wernet, D.V. Zante, T.J. Strazisar, W.T. John, P.S. Prahst, Characterization of the tip clearance flow in an axial compressor using 3-D digital PIV, Experiments in Fluids, 39 (2005) 743-753. [16] C. Hah, M. Voges, M. Mueller, H.-P. Schiffer, Characteristics of tip clearance flow instability in a transonic compressor, in: Turbo Expo: Power for Land, Sea, and Air, American Society of Mechanical Engineers, 2010, pp. 63-74. [17] M. Ostad, R. Kamali, Evaluating the Effects of Blade Tip Clearance in Various Stages on the Performance of an Axial Compressor, Journal of Applied Fluid Mechanics, 11(2) (2018) 475-481. [18] H. Khaleghi, M. Heinrich, M.J. Shahriyari, Circumferential casing treatment in a transonic fan, Amirkabir Journal of Mechanical Engineering, 53(7) (2021) 4189-4202. [19] M. Shahriyari, H. Khaleghi, URANS Simulation of Self-Recirculation Casing Treatment in a Transonic Compressor, Journal of Applied Fluid Mechanics, 17(5) (2024) 1073-1082. [20] H. Khaleghi, M.-A.S. Dehkordi, A.M. Tousi, Role of tip injection in desensitizing the compressor to the tip clearance size, Aerospace Science and Technology, 52 (2016) 10-17. [21] K. Kovach, D.M. Sandercock, S. Lieblein, Experimental Investigation of a Five-stage Axial-flow Research Compressor with Transonic Rotors in All Stages I: Compressor Design, National Advisory Committee For Aeronautics, 1954. [22] K. Kovach, D.M. Sandercock, Experimental Investigation of a Five-stage Axial-flow Research Compressor with Transonic Rotors in All Stages II: Compressor Over-all Performance, National Advisory Committee For Aeronautics, 1954. [23] Z. Mansouri, M. Yadegari, A. Bak Khoshnevis, Numerical investigation of the effects of installing four trip wires with different diameters on the mean and fluctuation velocities and characteristics of the wake around the circular cylinder, Journal of the Brazilian Society of Mechanical Sciences and Engineering, 45(9) (2023) 459. [24] M. Yadegari, An optimal design for S-shaped air intake diffusers using simultaneous entropy generation analysis and multi-objective genetic algorithm, The European Physical Journal Plus, 136(10) (2021) 1019. [25] M. Yadegari, A. Bak Khoshnevis, A numerical study over the effect of curvature and adverse pressure gradient on development of flow inside gas transmission pipelines, Journal of the Brazilian Society of Mechanical Sciences and Engineering, 42 (2020) 1-15. [26] Z. Jahani, H. Khaleghi, S. Tabejamaat, Using tip injection to stability enhancement of a transonic centrifugal impeller with inlet distortion, Journal of Applied Fluid Mechanics, 15(6) (2022) 1815-1824. | ||
|
آمار تعداد مشاهده مقاله: 745 تعداد دریافت فایل اصل مقاله: 495 |
||