中心线偏置隔离段内激波串迟滞特性研究

推进技术 ›› 2016, Vol. 37 ›› Issue (5): 864-870.

中心线偏置隔离段内激波串迟滞特性研究

熊冰,范晓樯,王振国

国防科学技术大学高超声速冲压发动机技术重点实验室，湖南长沙 410073,国防科学技术大学高超声速冲压发动机技术重点实验室，湖南长沙 410073,国防科学技术大学高超声速冲压发动机技术重点实验室，湖南长沙 410073

发布日期:2021-08-15
作者简介:熊冰，男，硕士生，研究领域为高超声速推进技术。
基金资助:
国家自然科学基金(11372347)。

Hysteresis Characteristics of Shock Train

Science and Technology on Scramjet Laboratory， National University of Defense Technology，Changsha 410073，China,Science and Technology on Scramjet Laboratory， National University of Defense Technology，Changsha 410073，China and Science and Technology on Scramjet Laboratory， National University of Defense Technology，Changsha 410073，China

Published:2021-08-15

摘要/Abstract

摘要： 采用定常与非定常数值计算相结合的方法研究了一种中心线偏置的隔离段流场，分析了不同反压作用下的激波串特征。通过模拟隔离段反压升高和降低的过程，研究了隔离段内激波串的迟滞特性，并比较了扩张比为0，10%，37%隔离段内迟滞特性的差异。结果表明，在来流马赫数2.0条件下，所研究隔离段内存在两种类型的迟滞现象；在同一反压条件下，降压路径对应的激波串更靠近管道入口。当反压接近隔离段所能承受的最大反压时，流场迟滞现象消失。隔离段扩张比越大(如37%)，激波串位置出现迟滞的反压范围越宽，迟滞量越小。最后利用流量匹配的观点从无粘角度解释了有粘流道内的激波串迟滞现象。

关键词: 隔离段；激波串迟滞；数值计算；中心线偏置；扩张比

Abstract: An investigation was conducted on flow fields in deflected center-line isolator by using steady and unsteady numerical simulation methods. The shock train structure was studied under different back-pressure. The hysteresis characteristics of shock train were analyzed with simulating the pressurized and depressurized process of isolator. The difference of hysteresis characteristics among isolators with 0，10% and 37% expanded ratio were compared. Results show that there are two different hysteresis phenomena in analyzed isolator at coming Mach 2.0. The position of shock train is nearer to isolator inlet in the depressurized process under the same back-pressure. The hysteresis phenomenon disappears when back-pressure approaches the limit pressure of isolator. To the isolator with larger expanded ratio (e.g. 37%)，the hysteresis phenomenon of leading-edge positon appears in a wider back-pressure range with smaller hysteresis value. In the end，an explaination for hysteresis phenomenon in viscous isolator was made by equaling the flux to an inviscid flow passage.

Key words: Isolator；Shock train hysteresis；Numerical simulation；Deflected center-line；Expanded ratio

熊冰,范晓樯,王振国. 中心线偏置隔离段内激波串迟滞特性研究[J]. 推进技术, 2016, 37(5): 864-870.

XIONG Bing,FAN Xiao-qiang,WANG Zhen-guo. Hysteresis Characteristics of Shock Train[J]. Journal of Propulsion Technology, 2016, 37(5): 864-870.

参考文献

[1] William H Heiser, David T Pratt. Hypersonic Airbreathing Propulsion[M]. USA: AIAA Education Series, 1994.
[2] 李博, 梁德旺. 高超声速进气道-隔离段反压引起不起动计算[J]. 推进技术, 2006, 27(5): 431-435. (LI Bo, LIANG De-wang. Calculation of Unstarted Flow in Hypersonic Inlet-Isolator with High Back Pressure[J]. Journal of Propulsion Technology, 2006, 27(5): 431-435.)
[3] 张堃元, 王成鹏, 杨建军, 等. 带高超进气道的隔离段流动特性[J]. 推进技术, 2002, 23(4): 311-314. (ZHANG Kun-yuan, WANG Cheng-peng, YANG Jian-jun. Investigation of Flow in Isolator of Hypersonic Inlet[J]. Journal of Propulsion Technology, 2002, 23(4): 311-314.)
[4] Wei Shyy, Michael J Rycroft. The Scramjet Engine Processes and Characteristics[M]. New York: Cambridge University Press, 2009.
[5] Om D, Childs M E. Multiple Transonic Shock Wave/Turbulent Boundary-Layer Interaction in a Circular Duct[J]. AIAA Journal, 1985, 23(10): 1506—1511.
[6] Kazuyasu Matsuo, Yoshiaki Miyazato, Heuy-Dong Kim. Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows[J]. Progress in Aerospace Scienes, 1999, 35 (1): 33-100.
[7] 刘兴洲. 中国超燃冲压发动机研究回顾[J]. 推进技术, 2008, 29(4): 385-395. (LIU Xing-zhou. Review of Scramjet Research in China [J]. Journal of Propulsion Technology, 2008, 29(4): 385-395.)
[8] 梁德旺, 李博. 高超声速进气道隔离段反压的前传模式及最大工作反压[J]. 空气动力学学报, 2006, 24(4): 454-460.
[9] 金亮, 吴先宇, 罗世彬, 等. 隔离段反压对激波串起始位置的影响[J]. 推进技术, 2008, 29(1): 54-57. (JIN Liang, WU Xian-yu, LUO Shi-bin, et al. Influence of Back Pressure on Location of Shock Train in Isolator[J]. Journal of Propulsion Technology, 2008, 29(1): 54-57.)
[10] Matsuo K, Mochizuki H, Miyazato Y, et al. Oscillatory Characteristics of a Pseudo-Shock Wave in a Rectangular Straight Duct[J]. Bulletin of the JSME, 1993, 36(2): 222-229.
[11] Ikui T, Mtsuo K, Nagai M, et al. Oscillation Phenomena of Peseudo Shock Waves [J]. Bulletin of the JSME, 1974, 17(112): 1278-1285.
[12] Billing F S, Waltrup P J, Stockbrige R D. Integral-Rocket Dual-Combustion Ramjets: a New Propulsion Concept[J]. Journal of Spacecraft and Rockets, 1980, 17(5): 416-424.
[13] 谭慧俊, 郭荣伟. 二维弯曲等截面管道中的激波串特性研究[J]. 航空学报, 2006, 27(6): 1039-1045.
[14] Tan H J, Sun S. Preliminary Study of Shock Train in a Curved Variable-Section Diffuser[J]. Journal of Propulsion and Power, 2008, 24(2): 245-252.
[15] Kawatsu K, Koike S, Kumasaka T, et al. Pseudo-Shock Wave Produced by Back Pressure in Straight and Diverging Rectangular Ducts[R]. AIAA 2005-2585.
[16] 李凤蔚. 空气与气体动力学引论[M]. 西安:西北工业大学出版社, 2007.(编辑:梅瑛)　　　　　　　　　　　　　*　收稿日期:2015-01-13；修订日期:2015-03-06。基金项目:国家自然科学基金(11372347)。作者简介:熊冰,男,硕士生,研究领域为高超声速推进技术。E-mail: marching@yeah.net