Study on the efficiency of a new central-type diffuser for hypersonic low density wind tunnel
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摘要: 扩压器是超/高超声速风洞的关键部件之一，直接影响风洞运行的费效比。然而，对于高超声速低密度风洞而言，试验运行参数范围大、试验气体密度又相对较低，常规的"收缩段-等直段-扩张段"的扩压器结构扩压作用不明显。提出一种带中心锥型扩压器新结构，并在Φ300 mm高超声速低密度风洞中进行扩压性能试验。研究了M16喷管小流量稀薄状态和M8喷管大流量近连续流状态下带中心锥型扩压器的扩压性能，同时，分析了试验段模型对扩压器扩压能力的影响。结果表明带中心锥结构的扩压器适用的风洞运行参数范围更广、扩压性能更优，能有效提高设备试验能力，可为高超声速风洞扩压器设计提供参考。Abstract: The diffuser is one of the key components of the supersonic and hypersonic wind tunnels, which directly affects the efficiency-cost ratio of the wind tunnel operation. However, for the hypersonic low density wind tunnel, the range of operating parameters is large and the test gas density is relatively low, and thus the effects of the conventional diffuser with "contraction section, equi-straight section and expansion section" are not obvious. In this paper, a new central-type diffuser structure is presented, and the efficiency of the central-type diffuser is tested at the Φ300 mm hypersonic low density wind tunnel for M16 small flow rate states and M8 large flow rate states. At the same time, the influence of the test section model on the diffuser's capacity is analyzed. The results show that the central-type diffuser has a wide range of operation parameters and a significant pressure increase efficiency, and can effectively improve the wind tunnel test capability. This study can provide a reference for the design of the hypersonic wind tunnel diffuser.
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Key words:
- low density wind tunnel /
- hypersonic /
- diffuser /
- diffuser efficiency
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图 1 低密度风洞扩压器前后静压典型变化图
Figure 1. Typical variation of static pressure before and after diffuser in low density wind tunnel
图 2 低密度风洞常规扩压器内典型压力分布云图
Figure 2. Typical static pressure distribution of conventional diffuser in low density wind tunnel
图 3 常规扩压器入口/出口径向压力和马赫数分布
Figure 3. Radial pressure and Mach number distribution at inlet and outlet of conventional diffuser
图 4 低密度风洞带中心锥型扩压器内典型压力分布云图
Figure 4. Typical static pressure distribution of central-type diffuser in low density wind tunnel
图 5 带中心锥型扩压器入口/出口径向压力和马赫数分布
Figure 5. Radial pressure and Mach number distribution at inlet and outlet of central-type diffuser
图 10 车次5和车次7冷却器前总压与静压对比
Figure 10. Comparison of total pressure and static pressure at pre-cooler of test 5 and 7
图 11 车次5冷却器前、扩压器前后及试验段静压变化
Figure 11. Variation of static pressure at pre-cooler, back-diffuser, pre-diffuser and test section of test 5
图 12 无中心锥冷却器前、扩压器前后及试验段静压变化
Figure 12. Variation of static pressure at pre-cooler, back-diffuser, pre-diffuser and test section without center cone
图 13 车次5冷却器前后中心线上马赫数变化情况
Figure 13. Variation of Mach number at center of pre- and back-cooler of test 5
图 14 车次26和车次27扩压器前后静压变化对比(没有模型时中心锥的影响)
Figure 14. Comparison of static pressure at pre- and back-diffuser of test 26 and 27(effect of center cone without test model)
图 15 车次24和车次30扩压器前后静压变化对比(有模型时中心锥的影响)
Figure 15. Comparison of static pressure at pre- and back-diffuer of test 24 and 30(effect of center cone with test model)
表 1 M16喷管相同试验参数不同试验条件下稳定运行时间
Table 1. Stable operation time of wind tunnel with the same test parameters but different test conditions at Mach number 16
车次号 试验条件 总温/K 总压/MPa 启动前真空压力/Pa t1s /s t2s /s 1 无模型无中心锥 936 1.15 49.5 232 179 2 无模型无中心锥 939 1.16 78.0 193 172 3 有模型无中心锥 931 1.17 41.6 243 177 4 有模型无中心锥 930 1.16 64.0 212 208 5 无模型有中心锥 935 1.19 56.4 225 260 6 无模型有中心锥 925 1.16 30.0 257 283 7 有模型有中心锥 920 1.17 41.6 241 275 8 有模型有中心锥 915 1.18 22.2 265 341 
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表 2 M8喷管不同试验条件下典型车次试验状态
Table 2. Typical test states at Mach number 8
车次号 试验条件 总温/K 总压/MPa 启动前真空压力/Pa 24 有模型, 有中心锥 498 1.63 671 26 无模型, 有中心锥 482 1.69 670 27 无模型, 无中心锥 489 1.65 389 30 有模型, 无中心锥 485 1.52 726
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