Effect of Thermal-Protection Ring on Flow and Aeroheating of Rudder Shaft
-
摘要: 空气舵缝隙内的舵轴是高速飞行器受热最严酷的部位之一。为减小舵轴的防热压力, 通过在舵轴周围设计防热环, 将舵轴的高热流区转移到防热环, 大幅减小舵轴的气动热载荷, 从而有效实现舵轴承力功能和防热环承热功能的分离。通过数值计算和试验研究分析了舵轴防热环的降热效果与机理, 获得以下结论: 通过有无防热环方案的仿真和试验对比, 表明了增加防热环能够明显降低舵轴热环境; 通过对舵缝隙内外流动的细致分析, 给出了舵轴防热环通过转移高热流区降低舵轴热流的降热机理; 通过不同舵偏和不同流态有无防热环方案数值计算的对比表明了防热环对舵轴热流的降低作用具有广泛适用性。Abstract: The rudder shaft in the gap is one of the most severely heated parts of high speed aircrafts. In order to reduce the thermal-protection pressure of rudder shaft, the heat load of rudder shaft is greatly reduced by transferring the high heat flux zone from the rudder shaft to the thermal-protection ring. It effectively realizes the separation of the force load bearing function of rudder shaft and the thermal load bearing function of thermal-protection ring. In this paper, three research aspects were carried out. Firstly, the comparison of thermal environment of rudder shaft with or without thermal-protection ring between simulations and experiments was studied and the results show that the heat flux of rudder shaft can be obviously decreased by using the thermal-protection ring. Secondly, it shows that the way of reducing the thermal environment of rudder shaft is feasible by transferringrudder shaft's high heat flux zone to thermal-protection ring. Thirdly, the influence of rudder deflection on reducing thermal environment of the rudder shaft was studied by analyzing the law of the thermal environment with different rudder deflections.
-
Key words:
- thermal-protection ring /
- rudder /
- rudder shaft /
- flow /
- aero-heating
-
图 4 有无防热环热流密度分布对比
Figure 4. Heat-flux results with and without thermal-protection ring
图 9 不同舵偏热流密度对比(无防热环)
Figure 9. Heat-flux comparison between different rudder deflections without thermal-protection ring
图 10 不同舵偏热流密度对比(有防热环)
Figure 10. Heat-flux comparison between different rudder deflections with thermal-protection ring
表 1 计算状态
Table 1. Calculation conditions
case Ma α/(°) Re∞/L /(m-1) T∞/K flow state 1 6.0 10 1.5×105 270 laminar 2 6.5 10 1.1×106 236 laminar/turbulent 3 6.6 10 5.4×106 221 turbulent 4 6.6 10 1.2×107 221 turbulent 
下载: 导出CSV
表 2 试验状态
Table 2. Experiment conditions
stage q/ (kW/m2) H/ (kJ/kg) α/(°) δ /(°) t/s 1 700 600 0 0 40 2 100 350 0 0 90 3 1 000 2 400 10 2 20 4 6 000 2 400 10 2 45
下载: 导出CSV
-
[1] 司于. 飞行器控制舵局部区域热环境与热防护研究[M]. 北京: 北京航空航天大学, 2013.Si Y. Thermal environment and thermal protection research of local area between control-flap and maneuver vehicle[M]. Beijing: Beihang University, 2013(in Chinese). [2] 吴宁宁, 康宏琳, 罗金玲. 高速飞行器翼舵缝隙激波风洞精细测热试验研究[J]. 空气动力学学报, 2019, 37(1): 133-139. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201901015.htmWu N N, Kang H L, Luo J L. Experimental study on fine thermal measurement of high speed aircraft wing rudder gapin shock wave tunnel[J]. Acta Aerodynamica Sincia, 2019, 37(1): 133-139(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201901015.htm [3] 黄尚坤, 肖素梅, 庞宇飞, 等. 高超声速飞行器钝舵缝隙流动数值模拟研究[J]. 航空工程进展, 2019, 10(2): 163-170. https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201408006.htmHuang S K, Xiao S M, Pang Y F, et al. Numerical investigation of flow in blunt-fin gap of hypersonic vehicle[J]. Advances in Aeronautical Science and Engineering, 2019, 10(2): 163-170(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201408006.htm [4] 李芳勇, 杨春信, 张兴娟. 高超声速飞行器舵轴热控方案设计[J]. 战术导弹技术, 2018, 4: 6-12. https://www.cnki.com.cn/Article/CJFDTOTAL-ZSDD201804002.htmLi F Y, Yang C X, Zhang X J. Thermal control design on a shaft in the hypersonic vehicle[J]. Tactical Missile Technology, 2018, 4: 6-12(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-ZSDD201804002.htm [5] 周佳. 超声速飞行器钝舵缝隙气动热环境研究[D]. 绵阳: 西南科技大学, 2014.Zhou J. Study of aerodynamic heating environment on blunt-fin gap of hypersonic vehicle[D]. Mianyang: Southwest University of Science and Technology, 2014(in Chinese). [6] 邓帆, 任怀宇, 谢峰, 等. 一种临近空间高超声速飞行器翼舵干扰研究[J]. 宇航学报, 2013, 34(6): 741-747. https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201306002.htmDeng F, Ren H Y, Xie F, et al. Research on wing-rudder interference of near-space hypersonic vehicle[J]. Journal of Astronautics, 2013, 34(6): 741-747(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-YHXB201306002.htm [7] Allen E, Winkelman. Experimental investigation of a fin protuberance partially immersed in a turbulent boundary layer at Mach 5[R]. AD-743903, 1972. [8] Tang G M. Heating characteristics of blunt swept fin-induced shock wave turbulent boundary layer interaction[J]. Acta Mechanica Sinica, 1998, 14(2): 139-146. doi: 10.1007/BF02487748 [9] 谭杰, 孙晓峰, 刘芙群, 等. 高超声速平板/空气舵热环境数值模拟研究[J]. 空气动力学学报, 2019, 37(1): 153-159. https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201901018.htmTan J, Sun X F, Liu F Q, et al. Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder configuration[J]. Acta Aerodynamica Sinica, 2019, 37(1): 153-159(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-KQDX201901018.htm [10] 艾邦成, 陈思员, 韩海涛, 等. 复杂构型前缘疏导热防护技术[J]. 气体物理, 2019, 4(1): 1-7. doi: 10.19527/j.cnki.2096-1642.0734Ai B C, Chen S Y, Han H T, et al. Complex dredging thermal protection structure for leading edge[J]. Physics of Gases, 2019, 4(1): 1-7(in Chinese). doi: 10.19527/j.cnki.2096-1642.0734 [11] 袁野, 曹占伟, 马伟, 等. 主动引射冷却对空气舵热环境影响的试验研究[J]. 导弹与航天运载技术, 2021, 6: 48-51. https://www.cnki.com.cn/Article/CJFDTOTAL-DDYH202106010.htmYuan Y, Cao Z W, Ma W, et al. Experimental research on the influence of the active ejection cooling on the thermal environment of the air rudder[J]. Missiles and Space Vehicles, 2021, 6: 48-51(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-DDYH202106010.htm [12] 檀妹静, 杨光, 李宇, 等. 整流帽布局对全动舵附近流动结构及热环境分布规律的影响[J]. 兵工学报, 2021, 42(8): 1648-1659. https://www.cnki.com.cn/Article/CJFDTOTAL-BIGO202108009.htmTan M J, Yang G, Li Y, et al. Influence of rectifying wedge on the flow structure and aerodynamics heating environment around all-movable rudder[J]. Acta Armamentarii, 2021, 42(8): 1648-1659(in Chinese). https://www.cnki.com.cn/Article/CJFDTOTAL-BIGO202108009.htm [13] 傅德薰, 马延文. 计算流体力学[M]. 北京: 高等教育出版社, 2002.Fu D X, Ma Y W. Computational fluid dynamics[M]. Beijing: Higher Education Press, 2002(in Chinese). [14] 阎超. 计算流体力学方法及应用[M]. 北京: 北京航空航天大学出版社, 2007.Yan C. Method and application of computational fluid dynamics[M]. Beijing: Beihang University Press, 2007(in Chinese). [15] Li Q, Nie L, Zhang K L, et al. Experimental investigation on aero-heating of rudder shaft within laminar/turbulent hypersonic boundary layers[J]. Chinese Journal of Aeronautics, 2019, 32(5): 1215-1211. -
点击查看大图
图(12) / 表(2)
计量
- 文章访问数: 126
- HTML全文浏览量: 106
- PDF下载量: 52
- 被引次数: 0
邮件订阅
RSS