局域能量注入对高超声速进气道流动影响研究

张黎; 李牧; 谭福利; 赵剑衡

doi:doi:10.3788/hplpb201426.031014

强激光与粒子束, 2014, 26 (3): 031014, 网络出版: 2014-03-31

局域能量注入对高超声速进气道流动影响研究

Influence of energy addition on scramjet inlet flow

论文大纲

张黎 ^*李牧谭福利赵剑衡

作者单位

中国工程物理研究院流体物理研究所, 四川绵阳 621900

高超声速进气道能量注入激波干扰高超风洞 scramjet inlet energy addition shock wave interaction hypersonic tunnel

摘要

研究了局域能量脉冲注入条件下高超声速进气道流场的扰动情况。数值模拟采用三维雷诺平均N-S方程，分别利用ROE格式和二阶中心格式对对流通量和粘性通量进行离散处理；用高斯-赛德尔隐式格式对方程进行时间推进求解，采用k-ε两方程模型用于湍流的数值模拟。开展了高超风洞平板流场能量注入实验，获取了高速纹影图像，并对实验结果与计算结果进行比较。研究表明，能量注入产生的冲击波能与高超流动产生的斜激波发生强烈干扰，脉冲能量的引入可能引起高超声速进气道流量俘获率产生剧烈震荡，从而导致进气道流场的性能急剧下降。

Abstract

Scramjet inlet flow disturbance was studied for the case when energy impulse was added on the wall of scramjet inlet. The flow is governed by the the 3-D Reynolds averaged Navier-Stokes equations. To split the viscosity flux and the convective flux of the N-S equations, the second order central scheme and the ROE scheme were adopted respectively. With the implicit Gauss-Seidel scheme, the code was advanced in time. The k-ε turbulence model was used for turbulence simulations. The characteristics of hypersonic flat with energy addition were tested in a hypersonic tunnel by applying a high speed schlieren system. The results show that the numerical pressure contour agrees well with the experimental schlieren photograph. Energy addition could induce strong shock wave interaction which might change the mass flow rate of scramjet inlet sharply. In other words, energy addition can decrease the performance of scramjet inlet flow and inlet unstart might take place at this rate.

参考文献

[1] 袁化成, 梁德旺. 抽吸对高超声速进气道起动能力的影响[J]. 推进技术, 2006, 27(6): 525-528. (Yuan Huacheng, Liang Dewang. Effect of suction on starting of hypers onic inlet. Journal of Propulsion Technology, 2006, 27(6): 525-528)

[2] Macheret S, Shneider M, Miles R. Virtual shapes in supersonic flow control with energy addition[J]. Journal of Propulsion and Power, 2008, 24(5): 900-915.

[3] 苏纬仪, 张新宇, 张堃元. 洛仑兹力控制高超声速进气道边界层分离的数值模拟[J]. 推进技术, 2011, 32(1): 36-41. (Su Weiyi, Zhang Xinyu, Zhang Kunyuan. Numerical investigation of Lorentz force control on hypersonic inlet boundary layer separation. Journal of Propulsion Technology, 2011, 32(1): 36-41)

[4] Yan H, Gaitonde D. Control of edney IV interaction by energy pulse[J]. AIAA Journal, 2006, 9(12): 562-573.

[5] 王殿恺, 洪延姬, 李倩. 激光能量主动控制高超声速进气道研究现状[J]. 激光杂志, 2012, 33(5): 1-2. (Wang Diankai, Hong Yanji, Li Qian. Development of laser energy controlling flow field of hypersonic inlet. Laser Journal, 2012, 33(5): 1-2)

[6] 王殿恺, 洪延姬, 李倩. 高重频激光能量注入提高进气捕获率的数值研究[J]. 强激光与粒子束, 2013, 25(7): 1715-1718. (Wang Diankai, Hong Yanji, Li Qian. Numerical study on increasing mass flow ratio by energy deposition of high frequency pulsed laser. High Power Laser and Particle Beams, 2013, 25(7): 1715-1718)

[7] 张黎, 陶彦辉, 王贵兵. 气流加热对气动光学效应的影响[J]. 强激光与粒子束, 2013, 25(2): 297-300. (Zhang Li, Tao Yanhui, Wang Guibing. Influence of airflow heating on aero-optic effects. High Power Laser and Particle Beams, 2013, 25(2): 297-300)

[8] 张黎, 贺佳, 谭福利. 激光加热金属板流固耦合数值模拟[J]. 强激光与粒子束, 2011, 23(4): 866-870. (Zhang Li, He Jia, Tan Fuli. Numerical simulation of metal plates under laser irradiation based on fluid-solid coupling. High Power Laser and Particle Beams, 2011, 23(4): 866-870)

[9] Abid R. Evaluation of two-equation turbulence modles for predicting transitional flows[J]. International Journal of Engineering Science, 1993, 31(1): 831-840.

[10] Frink N T, Parikh P, Pirzadeh S. A fast upwind solver for the Euler equations on three-dimensional unstructured meshes[R]. AIAA-91-0102, 1991.

张黎, 李牧, 谭福利, 赵剑衡. 局域能量注入对高超声速进气道流动影响研究[J]. 强激光与粒子束, 2014, 26(3): 031014. Zhang Li, Li Mu, Tan Fuli, Zhao Jianheng. Influence of energy addition on scramjet inlet flow[J]. High Power Laser and Particle Beams, 2014, 26(3): 031014.

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