تحلیل و شبیه سازی پدیده ی سرج در طبقه اول کمپرسور محوری توربین گاز GE-frame6

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشکده مهندسی مکانیک- دانشگاه زنجان

2 دانشکده فنی مهندسی دانشگاه زنجان

3 گروه مهندسی مکانیک، دانشکده فنی و مهندسی، دانشگاه زنجان

چکیده

یکی از نکات مهم در تحلیل عملکرد کمپرسور تخمین حد سرج است. چنانچه زاویه حمله هوا به هر دلیلی تغییر کند، جت‌های هوا از روی پره جداشده و باعث کوچک شدن سطح مقطع عبوری هوا و تغییر زاویه حمله هوا در پره بعدی می‌شود که به آن استال گویند. این عمل به همین صورت تکرار می‌گردد تا سرتاسر پره‌های یک ردیف را استال فراگیرد، در این صورت در پشت آن ردیف افت فشار روی می‌دهد و هوا از ردیف‌های بعدی که فشار زیادی دارند به سمت منطقه کم فشار برمی‌گردد که به آن سرج گویند. در این مقاله، شبیه‌سازی پدیده‌ی سرج در از پره‌های ردیف اول کمپرسور محوری توربین گاز GE-Frame 6 با زاویه حمله 34 درجه، به صورت گذرا و آشفته با مدل توربولانسی( k-w (sst انجام گرفته است. نتایج به دست آمده حاصل از بردارهای سرعت نشان می‌دهد که هنگام بروز سرج جریان معکوس که مهم‌ترین مشخصه وقوع سرج است، رخ داده و جریان به عقب بازمی‌گردد. همچنین در این مقاله، کدنویسی معادلات دیفرانسیل معمولی کوپل‌شده‌ی نرخ تغییرات فشار و جریان برای مقادیر مختلف پارامتر پایداری Bانجام گرفته است. مشاهده گردید که به ازای 6/ B=0 که کمتر از مقدار بحرانی است، استال دورانی رخ می‌دهد و فشار به صورت گذرا نوسان کرده و پس از چندین نوسان میرا می‌شود. درحالی‌که به ازای 6/ B = 1 که بیشتر از مقدار بحرانی بوده سرج عمیق رخ می‌دهد و فشار و جریان با دامنه ثابت نوسان می‌کنند.

کلیدواژه‌ها

موضوعات


عنوان مقاله [English]

Analysis and Simulation of Surge Phenomena in the First Stage of Axial Compressor of GE-frame 6 Gas Turbine

نویسندگان [English]

  • saeid nasiri 1
  • Esmaeil poursaeidi 2
  • Ehsan Khavasi 3
1 University of Zanjan / Mechanical Engineering Department
2 University of Zanjan / Mechanical Engineering Department
3 Mechanical engineering department, University of Zanjan
چکیده [English]

One of the important subjects in the analysis of compressor performance is estimating the surge limit. If the angle of attack changes for any reason, air jets separate from the blades and the cross-section area of the passing air becomes small and causes the alteration of the angle of attack in the next stage blades; this phenomenon is known as stall. When stall completed on a row, a pressure drop occurs at the rearward of that row. So, high-pressure air goes from the next row to the lower pressure area, which associated with a lot of noise and can cause the failure of the blades which is called surge. In this paper, the numerical simulation of surge in the first stage blades of the axial compressor of GE- Frame 6 gas turbine has been done. Simulations are done with a 34 degree angle of attack and k-ѡ SST turbulence model has been used. Obtained velocity vectors indicate that during the surge, the reverse flow which is the most important characteristic of surge occurs and the flow returns backward. Also, in this paper, the coupled ordinary differential equations of pressure and flow changes for different values of the stability parameter B has been solved. It was found that for B = 0.6, which is less than the critical value, rotating stall occurs and the pressure fluctuations damp after several fluctuations. While for B = 1.6, which is more than its critical value, a deep surge occurs and the pressure and flow disturbances fluctuate with constant amplitudes.

کلیدواژه‌ها [English]

  • Axial compressor
  • stall
  • surge
  • back flow
  • surge cycle
[1] B. Badrzadeh, M. Hogdahl, E. Isabegovic, "Transients in Wind Power Plants—Part I: Modeling Methodology and Validation", IEEE Trans on Industry Applications, vol.48, no. 2, pp.794-807, 2012.
[2]  H. Sheng , W.Huang, T.Zhang, X. Huang, “Robust Adaptive Fuzzy Control of Compressor Surge Using Backstepping”, Arabian Journal for Science and Engineering, vol.39, no.12, pp.9301-9308, 2014
[3] J. M. S., E. J. Mo, and K. W. Lee, “Fuzzy PI Controller for Turbojet Engine of Unmanned Aircraft", Springer- Verlag Berlin Heidelberg, Hankuk Aviation University, 2007.
[4] H.W. Emmons, C.E, Pearson and H.P. Grant ,Compressor surge and stall propagation, Transactions of the ASME 77,455-469,1955.
[5] E. M. Greitzer, Surge and Rotating Stall in Axial Flow Compressors Part I: Theoretical Compression System Model, Journal of Engineering for Power, ASME,1976.
[6] E. M. Greitzer, Surge and Rotating Stall in  Axial  Flow Compressors Part II: Experimental Results and Comparison With Theory, Journal of Engineering for Power, ASME,1976.
[7] M. W. Davis, A stage-by-stage post-stall compression system modeling technique: methodology, validation, and application, Ph.D. thesis, Virginia Polytechnic Institute and state university, 1987.
[8]  M. Morini, M. Pinelli, and M. Venturini, “Development of a one-dimensional modular dynamic model for the simulation of surge in compression systems,” Journal of Turbomachinery, vol. 129, no. 3, pp. 437–447, 2007.
[9] J. Galindo, A. Tiseira, J. Arnau, et al., “On-engine measurement of turbocharger surge limit,” Experimental Techniques 37 47–54 (2013).
[10] R. Bontempo, M. Cardone, M. Manna, G. Vorraro, “A statistical approach to the analysis of the surge phenomenon, ” Energy 124 502-509 (2017).
[11] R. Kabral, M. Abom, “Investigation of turbocharger compressor surge inception bymeans of an acoustic two- port model, ”.Journal of Sound and Vibration 412 270- 286 (2018).
[12] Moore, F.K. A theory of rotating stall of multistage axial compressors: Part I-Small disturbances. Journal of Engineering for Gas Turbines and Power 106, 313-320 (1984a).
 [13] Moore, F.K. A theory of rotating stall of multistage axial compressors: Part II-Finite disturbances. Journal of Engineering for Gas Turbines and Power 106, 321-326(1984b).
 [14] J. T. Gravdahl, O. Egeland, S. O. Vatland, “Drive torque actuation surge control of centrifugal compressor”, Journal of engineering 2002.
[15] E. Hellstrom, H. Ossareh, B. Xiao, M. Santillo, “ Characterizing and Detecting Surge and Co-Surge in Automotive Compressors ,” IFAC-PapersOnLine 49-11 702–707 (2016).
[16] E. Munari, M. Morini, M. Pinelli, p. Spina, “Experimental investigation and modeling of surge in a multistage compressor,” Energy Procedia 105 1751 – 1756 (2017 )
[17]  M.Righi, V.Pachidis,  L.Könözsy,  L.Pawsey  “ Three- dimensional through-flow modelling of axial flow compressor rotating stall and surge,” Aerospace Science and Technology 78 271–279 (2018).
[18]   T.WANG, X .XUE, T. ZHANG, B.YANG, “Mechanism of stall and surge in a centrifugal compressor with a variable vaned diffuser,” Chinese Journal of Aeronautics, 31(6): 1222–1231 (2018).
[19]  S.Pakle, K.Jiang, “Design of a high-performance centrifugal compressor with new surge margin improvement technique for high speed turbomachinery,” Propulsion and Power Research;7(1):19–29 (2018).
[20]   S. Niazi, “Numerical simulation of rotating stall and surge alleviation in axial compressors” , Thesis for the degree Doctor of Philosophy ,Aerospace Engineering, Georgia Institute of Technology, 2000.
[21]   E.M. Greitzer )1985a(. An introduction to unsteady flow in turbomachines. In: Thermodynamics and Fluid Mechanics of turbomachinery Vol. II of NATO ASI Series, Series E: Applied Sciences - No. 97B. pp. 967- 1024. Martin Nijhoff Publishers,1985.
[22]   C. LI, Siqi XU, Zhiqi HU, “experimental study of surge and rotating stall occurring in highspeed multistage axial compressor,” Procedia Engineering 99 1548 –1560 ( 2015).
[23]  I. J. Day, “Axial compressor performance during surge,” AIAA Journal of Propulsion and Power, vol. 10, no. 3, pp. 329–336, 1994.