发汗冷却对高马赫数压缩拐角流动结构与气动热的影响

胡琛浩; 孙昊天; 张建伟; 邱云龙; 江中正; 陈伟芳

doi:10.13224/j.cnki.jasp.20250471

发汗冷却对高马赫数压缩拐角流动结构与气动热的影响

doi: 10.13224/j.cnki.jasp.20250471

胡琛浩^1,,
孙昊天¹,
张建伟³,
邱云龙^{1, 2,*, ,},
江中正¹,
陈伟芳¹

1.
浙江大学航空航天学院，杭州 310027
2.
浣江实验室先进飞行器研究中心，浙江诸暨 311800
3.
北京空天技术研究所空天飞行技术全国重点实验室，北京 100074

基金项目: 国家自然科学基金（U24B2007，92471109）；空天飞行技术全国重点实验室开放基金（118009564174）；杭州城西科创大走廊创新发展专项资金

详细信息

作者简介:
胡琛浩（2000-），男，硕士生，主要从事高速飞行器主动流动控制方面的研究。E-mail：22324076@zju.edu.cn

通讯作者:
邱云龙（1992-），男，研究员，博士，主要从事流动控制与热管理方面的研究。E-mail：qyl1992@zju.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2025-10-16
- 网络出版日期: 2026-01-24

Effects of transpiration cooling on flow structure and aerothermal environment of high Mach number compression corner

1.
School of Aeronautics and Astronautics，Zhejiang University，Hangzhou 310027，China
2.
Advanced Aircraft Research Center，Huanjiang Laboratory，Zhuji Zhejiang 311800，China
3.
National Key Laboratory of Aerospace Flight Technology，Beijing Aerospace Technology Research Institute，Beijing 100074，China

摘要

摘要:
针对高马赫数压缩拐角的降热需求，通过数值模拟研究了来流马赫数为11.63条件下气体发汗对15°压缩拐角流动结构和气动热的影响。计算结果表明：气体发汗会显著增大其作用区域及下游区域的边界层厚度，降低边界层内的速度梯度并增大局部压力。当发汗位置位于流动分离区上游或内部时，在发汗作用下压缩拐角的分离区显著扩大，而当发汗位置位于流动分离区下游时，气体发汗对压缩拐角的流动分离特性几乎无影响。压缩拐角流动结构的变化显著影响了其气动热分布，边界层增厚降低了边界层内的温度梯度，从而降低了其作用区域及下游区域的壁面热流。为实现最优降热效果，发汗冷却应覆盖热流峰值附近的高热区域，同时其作用局限于下游区域，以避免分离区扩大，从而稳定热流峰值位置并有效降低峰值热流。
- 发汗冷却 /
- 高马赫数 /
- 压缩拐角 /
- 边界层分离 /
- 激波边界层干扰 /
- 气动热
Abstract:
In order to meet the thermal reduction requirements of high Mach number compression corners, numerical simulations were carried out to study the effects of gas transpiration on the flow structure and aerothermal environment of a 15° compression corner at a free stream Mach number of 11.63. The results showed that gas transpiration significantly increased the boundary layer thickness in both its active and downstream regions, reduced the velocity gradient within the boundary layer, and augmented the local pressure. When the transpiration location was positioned upstream or within the separation zone, gas transpiration led to a significant enlargement of the separation region. In contrast, when the transpiration location was positioned downstream the separation zone, gas transpiration had a negligible influence on the separation characteristics. Variations in the flow structure were found to significantly influence the wall heat flux distribution. The thickening of the boundary layer reduced the temperature gradient within it, thereby lowering the wall heat flux in both the transpiration region and the downstream region. To achieve optimal thermal reduction, transpiration cooling should cover the high heat flux region near the peak heat flux, while its effect remains confined to the downstream region to prevent the expansion of the separation zone, thereby stabilizing the peak heat flux location and effectively reducing the peak heat flux.
- transpiration cooling /
- high Mach number /
- compression corner /
- boundary layer separation /
- shock wave/boundary layer interaction /
- aerothermal environment

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图 1 压缩拐角外形示意图

Figure 1. Schematic of compression corner

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图 2 Ma_∞=11.63条件下15°压缩拐角流动结构

Figure 2. Flow structure of 15° compression corner at Ma_∞=11.63

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图 3 发汗冷却区域分布示意图

Figure 3. Schematic of transpiration cooling regions

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图 4 压缩拐角二维结构网格

Figure 4. Two-dimensional structured mesh for compression corner

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图 5 不同网格条件下的壁面压力和热流分布

Figure 5. Distributions of wall pressure and heat flux under different grids

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图 6 数值计算与实验测量^[26]的壁面压力和热流分布

Figure 6. Distributions of wall pressure and heat flux from numerical and experimental results^[26]

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图 7 发汗位置位于x=0.110 m时不同发汗工质的马赫数云图对比

Figure 7. Comparison of Mach number contours under different transpiration coolants with transpiration at x=0.110 m

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图 8 发汗位置位于x=0.110 m时不同发汗工质的壁面斯坦顿数分布

Figure 8. Distributions of wall Stanton number under different transpiration coolants with transpiration at x=0.110 m

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图 9 有无发汗（x=0.110 m，原始分离点上游）条件下的马赫数云图

Figure 9. Mach number contours with and without transpiration at x=0.110 m, upstream of the original separation point

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图 10 有无发汗（x=0.110 m，原始分离点上游）条件下不同位置的流向速度沿壁面法向分布

Figure 10. Wall-normal distributions of streamwise velocity at different locations with and without transpiration （x=0.110 m, upstream of the original separation point）

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图 11 发汗位置位于x=0.450, 0.600, 0.609 m时的马赫数云图对比

Figure 11. Comparison of Mach number contours under different transpiration location at x=0.450, 0.600, 0.609 m

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图 12 发汗位置位于x=0.450, 0.600, 0.609 m时的壁面压力系数分布

Figure 12. Distributions of wall pressure coefficient under different transpiration location at x=0.450, 0.600, 0.609 m

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图 13 不同发汗位置条件下的壁面斯坦顿数分布

Figure 13. Distributions of wall Stanton number at different transpiration locations

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图 14 发汗位置位于x=0.110 m时不同发汗流量的马赫数云图对比

Figure 14. Comparison of Mach number contours under different transpiration flow rates with transpiration at x=0.110 m

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图 15 发汗位置位于x=0.609 m时不同发汗流量的马赫数云图对比

Figure 15. Comparison of Mach number contours under different transpiration flow rates with transpiration at x=0.609 m

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图 16 发汗位置位于x=0.110 m和x=0.609 m时不同发汗流量的壁面斯坦顿数分布

Figure 16. Distributions of wall Stanton number under different transpiration flow rates with transpiration at x=0.110 m and x=0.609 m

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表 1 发汗冷却计算状态

Table 1. Computation conditions of transpiration cooling

发汗冷却区域起始坐标x/m	发汗分数F/%	发汗工质	发汗冷却区域长度L/m
0.110	0.4，0.8	氩气，空气，氦气	0.055
0.450	0.8	空气	0.055
0.600	0.8	空气	0.055
0.609	0.4，0.8	空气	0.055
0.660	0.8	空气	0.055

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表 2 压缩拐角计算网格参数

Table 2. Grid parameters of compression corner

编号	网格分布	网格量	第1层网格高度/10⁻⁷ m	Re_grid
1	681×121	86400	10	0.552
2	881×181	166500	5	0.276
3	1321×241	326400	1	0.055

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表 3 不同发汗位置条件下的分离区参数及气动阻力

Table 3. Parameters of separation zone and drag variation at different transpiration locations

x₀/m	L_s/m	D_p/N	$ {\eta }_{ （D\text{p}） } $/%	D_f/N	$ {\eta }_{ （D\text{f}） } $/%
无发汗	0.188	61.00	0	8.00	0
0.110	0.361	59.02	−3.25	5.63	−29.62
0.450	0.430	57.71	−5.39	5.52	−31.01
0.600	0.418	57.79	−5.26	5.18	−35.24
0.609	0.204	60.85	−0.25	6.59	−17.66
0.660	0.188	61.12	0.20	6.95	−13.09

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表 4 不同发汗位置条件下的降热效果

Table 4. Effects of heat reduction at different transpiration locations

发汗冷却区域起始坐标x/m	发汗分数F/%	峰值斯坦顿数/ 10⁻³	峰值热流降热率/%
无发汗	0	5.63	0
0.110	0.8	4.68	−16.87
0.450	0.8	4.42	−21.49
0.600	0.8	4.32	−23.27
0.609	0.8	3.82	−32.15
0.660	0.8	5.58	−0.89

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表 5 发汗位置位于x=0.110 m和x=0.609 m时不同发汗流量的降热效果对比

Table 5. Comparison of heat reduction effects under different transpiration flow rates with transpiration at x=0.110 m and x=0.609 m

发汗冷却区域起始坐标x/m	发汗分数F/%	峰值斯坦顿数/10⁻³	峰值热流降热率/%
无发汗	0	5.63	0
0.110	0.4	5.18	−7.99
0.110	0.8	4.68	−16.87
0.609	0.4	4.61	−18.12
0.609	0.8	3.82	−32.15

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