Scramjet尾喷管几何调节方案的计算与实验研究

推进技术 ›› 2013, Vol. 34 ›› Issue (9): 1158-1164.

Scramjet尾喷管几何调节方案的计算与实验研究

葛建辉,徐惊雷,庞丽娜,莫建伟

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:葛建辉(1985—),男,硕士生,研究领域为高超声速进排气气动力学。E-mail:jianhuig@nuaa.edu.cn
基金资助:
国家自然科学基金(90916023)。

CFD and Experimental Investigation for an Adjustable Scramjet Nozzle

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016,China

Published:2021-08-15

摘要/Abstract

摘要： 高超声速飞行器飞行接力点和巡航结束点尾喷管冷、热态俯仰力矩差较大,给飞行器的飞行姿态控制造成严重影响。为了减小喷管冷、热态俯仰力矩差,提出了在喷管上膨胀面末端增加移动板进行调节的方案,并进行了详细的三维数值模拟和相应的风洞缩比冷流实验研究。计算结果表明,Ma=4.5时,调节移动板伸出400mm,喷管冷、热态力矩差最大减小21.74%,推力系数损失1.64%；Ma=6.5时,调节移动板喷管冷、热态力矩差可降低77.59%,而推力系数只减小1.35%,调节收益非常明显。最后通过将喷管各调节状态下的冷流缩比实验壁面压力数据与计算结果的对比,证明了该调节方案的计算方法及其结果是可靠的,同时得出该调节方案可以有效地降低冷、热态力矩差的结论。 

关键词: 超燃冲压发动机;尾喷管;几何调节;俯仰力矩差;数值模拟;实验研究 

Abstract: The difference of pitch moment under cold and hot conditions can be changed greatly when the hypersonic vehicle works at relay point and cruising end point, which will cause the big problem of the vehicle control. In order to decrease the difference of cold/hot pitch moment, an adjustment method with a slide wall at the end of nozzle up expansion wall was proposed, and was investigated by using CFD and cold flow experiment of scaled wind tunnel, and it was proven to be effective to decrease the difference of cold/hot pitch moment. The computed results show that in Mach 4.5, the difference between the cold and hot pitch moment is reduced by 21.74% at the maximum and the thrust coefficient penalty is only 1.64% when the sliding wall is extended 400mm, as the same sliding wall out length in Mach 6.5, the difference between the cold and hot pitch moment decreases by 77.59% and the thrust coefficient decreases by 1.35%, which is proven to be highly efficient in Mach 6.5. Finally the computed results are compared with experimental data. 

Key words: Scramjet engine; Nozzle; Geometry adjustment; Difference of pitch moment; Numerical simulation; Experiment

葛建辉,徐惊雷,庞丽娜,莫建伟. Scramjet尾喷管几何调节方案的计算与实验研究[J]. 推进技术, 2013, 34(9): 1158-1164.

GE Jian-hui, XU Jing-lei, PANG li-na, MO Jian-wei. CFD and Experimental Investigation for an Adjustable Scramjet Nozzle[J]. Journal of Propulsion Technology, 2013, 34(9): 1158-1164.

参考文献

[1] Deere K A, Asbury S C.An Experimental and Computational Investigation of a Translating Throat Single Expansion Ramp Nozzle[R].AIAA 96-2540.
[2] Lederer R, Kruger W.Nozzle Development as a Key Element For Hypersonics[R].AIAA 93-5058.
[3] Lederer R.Testing the Actively Cooled Fully Variable Hypersonic Demonstrator Nozzle[R].AIAA 96-4550.
[4] Chevalier A, Levine V M, Bouchez,et al.French-Russian Partnership on Hypersonic Wide Range Ramjets[R].AIAA 96-4554.
[5] Baranovsky S I, Gilevith, Davidenko D,et al.A Program of the Scramjet Design and Optimization[R].AIAA 91-5073.
[6] Baranovsky S I, Levin V M, Avrashkov V N.Gasdynamic Features of Supersonic Kerosene Combustion in a Model Combustion Chamber[R].AIAA 90-5268.
[7] Baranovsky S I, Levin V M, Nadvorsky A S,et al.Heat Transfer in Supersonic Coaxial Reacting Jets[J].Heat Mass Transfer, 1990,3(4):641-648.
[8] Levin V M.Gas Dynamics of Flow Structure in a Channel under Thermal and Mechanical Throttling[C].Beijing:1st Int.Symposium on Eperimental and Computational Aerodynamics of internal Flows , 1990.
[9] Baranovsky S, Levin V M.Wide Range Combustion Chamber of Ramjet[R].AIAA 91-5094.
[10] 晏至辉,刘卫东.超燃冲压发动机尾喷管数值分析[J].导弹与航天运载技术,2006,(5):50-52.
[11] 晏至辉.超燃冲压发动机尾喷管仿真和实验研究[D].长沙:国防科学技术大学,2005.
[12] 黄伟,罗世彬,王振国.超燃冲压发动机尾喷管构型参数灵敏度分析[J].推进技术,2009,0(6):691-695.(HUANG Wei, LUO Shi-bing, WANG Zhen-guo.Parametric Sensitivity Analysis of Scramjet Nozzle Configuration[J].Journal of Propulsion Technology, 2009,0(6):691-695.)
[13] 李建平,宋文燕,陈亮.超燃冲压发动机尾喷管性能研究[J].机械设计与制造,2008,2(2):95-97.
[14] Goeing M.Nozzle Design Optimization by Method-of-Characteristics[R].AIAA 90-2024.
[15] 张艳慧.非对称大膨胀比喷管设计及性能分析[D].南京:南京航空航天大学,2006.
[16] 谭杰, 金捷, 杜刚, 等.过膨胀单边膨胀喷管试验和数值模拟[J].推进技术,2009,0(3):292-296.(TAN Jie, JIN Jie, DU Gang, et al.Experimental and Computational Investigation of an Over-Expanded Single-Expansion-Ramp-Nozzle[J].Journal of Propulsion Technology , 2009,0(3):292-296.)