超声速连续风洞喷管启动过程分析

推进技术 ›› 2015, Vol. 36 ›› Issue (1): 24-29.

超声速连续风洞喷管启动过程分析

陶渊,范晓樯,刘俊林

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:陶渊(1990—)，男，硕士生，研究领域为高超声速空气动力学。
基金资助:
国家自然科学基金(11372347)。

Studies on Starting Process of a Continuous Supersonic Wind

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： 为深入了解超声速连续风洞喷管启动过程中流场结构变化情况，采用数值计算与风洞试验相结合的方法，对连续风洞Ma=4.35喷管进行了研究。分析表明，喷管非定常启动过程可分为“初始蓄气”、“激波串推进”、“核心流推出”、“准稳定增压”四个阶段。其中，“初始蓄气”阶段，气体总压在收缩段不断增加，马赫数在喉道附近逐渐增大；“激波串推进”阶段，激波串结构形成并逐渐向下游推进；“核心流推出”阶段，核心流部分推出边界，但流场结构变化缓慢；“准稳定增压”阶段耗时占整个启动过程耗时的60%以上，且流场结构与稳定阶段流场结构趋于一致，但喷管内各点压力仍不断上升。同时与定常流场对比分析，进一步说明了各阶段流场特点，并指出对“核心流推出”和“准稳定增压”阶段采用定常分析方法的必要性。

关键词: 连续风洞；喷管；启动过程；非定常

Abstract: To further explore the structural changes of flow field during the starting process of a continuous supersonic wind tunnel nozzle，a wind tunnel nozzle with the exit Mach number of 4.35 was investigated numerically and experimentally. The analysis shows that it was not difficult to divide the unsteady starting process of wind tunnel nozzle into four stages，which were named initial accumulation，development of shock train，extrusion of flow，pseudo-stabilization in turn. Thereinto，at the first stage，the pressure in the contraction increased，and the Mach number near the throat rose gradually. At the second stage，a shock train structure was formed and developed. At the third stage，the main flow was beyond the outlet boundary partly. The final stage accounted for more than 60% of the nozzle starting time，and the pressure in the nozzle went up continually，while the flow structure was stable. At the same time，compared with the steady results，this paper further emphasized the characters of each stage，and demonstrated that it is necessary to use the steady result to analyse the starting process at the stage of extrusion of flow，pseudo-stabilization.

Key words: Continuous wind tunnel；Nozzle；Starting process；Unsteady

陶渊,范晓樯,刘俊林. 超声速连续风洞喷管启动过程分析[J]. 推进技术, 2015, 36(1): 24-29.

TAO Yuan,FAN Xiao-qiang,LIU Jun-lin. Studies on Starting Process of a Continuous Supersonic Wind[J]. Journal of Propulsion Technology, 2015, 36(1): 24-29.

参考文献

[1] Smith C E. An Analytic Study of the Starting Process in a Hypersonic Nozzle[D]. Stanford: Stanford University, 1962.
[2] Smith C E. The Starting Process in a Hypersonic Nozzle [J]. Journal of Fluid Mechanics, 1966, 24: 625-640.
[3] Jacobs P A. Numerical Simulation of Transient Hypervelocity Flow in an Expansion Tube[R]. NASA-CR-189615, 1992.
[4] Jacobs P A. Transient, Hypervelocity Flow in an Axisymmetric Nozzle [R].NASA-CR-187496, 1991.
[5] Jacobs P A. Simulation of Transient Flow in a Shock Tunnel and a High Mach Number Nozzle [R]. NASA-CR-187606, 1991.
[6] 张小庆, 杨富荣, 鲍伟义, 等. 直连式脉冲燃烧风洞起动过程研究[J]. 实验流体力学, 2009, 23(3): 63-67.
[7] 张小庆, 乐嘉陵, 许明恒. 超声速脉冲风洞起动过程数值模拟[J]. 西南交通大学学报, 2008, 43 (6): 751-755.
[8] 陈立红, 张新宇, 顾洪斌. 扩压段对高超声速推进风洞起动的影响 [J]. 推进技术, 2004, 25(5): 430-434 (CHEN Li-hong, ZHANG Xin-yu, GU Hong-bin.Investigation for Effect of Supersonic Diffusers on the Start of the Hypersonic Propulsion Test Facility [J]. Journal of Propulsion Technology, 2004, 25 (5): 430-434.)
[9] 范晓樯, 贾地, 冯定华, 等. 脉冲风洞中进气道起动过程试验研究 [J]. 推进技术, 2007, 28 (1): 60-64. (FAN Xiao-qiang, JIA Di, FENG Ding-hua, LI Hua. Experimental Investigation on Starting Process of Hypersonic Inlet in Gun Tunnel [J]. Journal of Propulsion and Power, 2007, 28 (1): 60-64.)
[10] Ackroyd J A D. Studies on the Running Time in a Shock Tube and Shock Tunnel[D]. London: University of London, 1964.
[11] YANG G W, HU Z M, JIANG Z. Starting Nozzle Flow Simulation Using K-G Two-Equation Turbulence Model[C]. Beijing: Proceedings of the 24th International Symposium on Shock Waves, 2004.
[12] Bird G A. The Effect of Wall Shape on the Degree of Reinforcement of a Shock Wave Moving into a Converging Channal [J]. Journal of Fluid Mechanics, 1959, 5:60-74.
[13] 周文祥, 黄金泉, 周人治. 拉瓦尔喷管计算模型的改进及其整机仿真验证 [J]. 航空动力学报, 2009, 24(11): 2602-2606.
[14] Shimshi E, Ben-Dor G, Levy A. Viscous Simulation of Shock-Reflection Hysteresis in Overexpanded Planar Nozzles[J]. Journal of Fluid Mechanics, 2009, 635: 189-206.
[15] Matsuo K, Miyazato Y, Kim H-D. Shock Train and Pseudo-Shock Phenomena in Internal Gas Flows [J]. Progress in Aerospace Sciences, 1999, 35:33-100.
[16] 陈吉明, 任玉新. 超声速风洞扩压段激波串现象的数值模拟 [J]. 清华大学学报, 2007, 47:264-267.
[17] 李桦, 范晓樯, 丁猛. 超声速扩压器中激波串结构的数值模拟 [J]. 国防科技大学学报, 2002, 24: 18-21.
[18] Neumann E P, Lustwerk F. Supersonic Diffusers for Wind Tunnls[J]. Journal of Applied Mechanics, 1949, 16 (2): 195-202.
[19] Neumann E P, Lustwerk F. High Efficiency Supersonic Diffusers[J]. Journal of Aeronautical Sciences, 1951, 18(6): 369-374.(编辑:朱立影)*　收稿日期:2013-11-25；修订日期:2014-03-07。基金项目:国家自然科学基金(11372347)。作者简介:陶渊(1990—),男,硕士生,研究领域为高超声速空气动力学。E-mail: york_tao@126.com