非对称喷管流动分离的预测

Abstract

Abstract: The asymmetric ramp nozzle is a key component of the scramjet engine and turbine based combined cycle(TBCC) engine, but it often exhibits serious flow separation in the nozzle off-design point. Focusing on the flow separation in an over-expended asymmetric ramp nozzle, new criteria of flow separation based on 2-D computational fluid dynamics (CFD) technique is obtained with reference to the criteria of flow separation in a symmetrical nozzle. Furthermore, their universality and accuracy are verified by testing other asymmetric ramp nozzle models working in over-expended conditions. The results indicate that the new criteria can also be used for other different asymmetric ramp nozzles. The new criteria and test data show excellent agreement by the range of the experiment pressure ratio with root mean square error of 3.68%,which provides proof that the new criteria used for flow separation prediction in asymmetric ramp nozzle are reliable.

Key words: scramjet engine, asymmetric ramp nozzle, flow separation, separation criteria, over-expension

CLC Number:

V231.3

GE Jianhui, XU Jinglei, WANG Mingtao, MO Jianwei. Prediction of Flow Separation in Asymmetric Ramp Nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(8): 1394-1399.

References

[1] Edwards C L Q, Small W J, Weidner J P, et al. Studies of scramjet/airframe integration techniques for hypersonic aircraft. AIAA-1975-58, 1975.
[2] Mo J W, Xu J L, Li C. The numerical study of over-under TBCC exhaust system. The 1st Conference of Turbo/Ramjet Combined Cycle Engine, 2008. (in Chinese) 莫建伟, 徐惊雷, 李超. 并联式TBCC发动机排气系统不同工况下的性能研究. 第一届涡轮冲压组合动力发动机会议, 2008.
[3] Abdellah H, Marcello O. Nozzle flow separation. Shock Waves, 2009, 19(3): 163-169.
[4] Schilling M T. Flow separation in a rocket nozzle. Buffalo: State University of New York, 1962.
[5] Lawrence R A. Symmetrical and unsymmetrical flow separation in supersonic nozzles. Dallas: Southern Methodist University, 1967.
[6] Nave L H, Coffey G A. Sea-level side loads in high-area-ratio rocket engines. AIAA-1973-1284,1973.
[7] Erengil M E, Dolling D S. Unsteady wave structure near separation in a Mach 5 compression ramp interaction. AIAA Journal, 1991, 29(5): 728-735.
[8] Dumnov G. Investigation on separation and side loads. Internal DLR Report, 1997.
[9] Ostlund J. Flow processes in rocket engine nozzles with focus on flow separation and side-loads. Technical Reports from Royal Institute of Technology Stockholm, 2002.
[10] Hagemann G, Preuss A, Grauer F, et al. Flow separation and heat transfer in high area ratio nozzles. AIAA-2004-3684, 2004.
[11] Verma S B. Shock unsteadiness in a thrust optimized parabolic nozzle. Shock Waves, 2009, 19(3): 193-212.
[12] Stark R H. Flow separation in rocket nozzles, a simple criteria. AIAA-2005-3940, 2005.
[13] Summerfield M, Foster C, Swan W. Flow separation in over expanded supersonic exhaust nozzles. Jet Propulsion, 1954, 24(5): 319-321.
[14] Schmucker R H. Status of flow separation prediction in liquid propellant rocket nozzles. NASA TM X-64890, 1974.
[15] Zhang K Y, Zhang R X, Xu H. Investigation of single expansion ramp nozzle. Journal of Propulsion Technology, 2001, 22(5): 380-382 (in Chinese) 张堃元, 张荣学, 徐辉. 非对称大膨胀比喷管研究. 推进技术, 2001, 22(5): 380-382.
[16] Tan J, Jin J, Du G, et al. Experimental and computational investigation of a over-expanded single-expansion-ramp-nozzle. Journal of Propulsion Technology, 2009, 30(3): 292-296. (in Chinese) 谭杰, 金捷, 杜刚, 等. 过膨胀单边膨胀喷管试验和数值模拟. 推进技术, 2009, 30(3): 292-296.

Prediction of Flow Separation in Asymmetric Ramp Nozzle

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