General performance of 0.6m continuous transonic wind tunnel
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摘要: 中国空气动力研究与发展中心（CARDC）0.6m连续式跨声速风洞是一座采用干燥空气作为试验介质的变密度回流式风洞，设计方案采用了宽工况压缩机及其与风洞一体化设计、半柔壁喷管、低噪声跨声速试验段、指片再入调节片式主流引射缝、高性能换热器和三段调节片加可调中心体式二喉道等新型技术。通过风洞总体性能调试，获取了风洞安全运行边界及总体性能，得到了风洞各关键部段性能参数。调试结果表明，风洞总体和各部段性能均达到预期设计技术要求；压缩机、换热器和各辅助系统设备运行性能良好；实现稳定段总压运行范围15~250kPa，总压控制精度优于0.2%；实现试验段Ma运行范围为0.144~1.640，马赫数控制精度优于0.002；轴向马赫数分布均方根偏差优于设计指标（Ma ≤ 1.0时，σMa < 0.002，1.0 < Ma ≤ 1.6时，σMa < 0.008）的要求；当试验Ma ≥ 0.5时，试验段核心气流脉动压力系数ΔCp < 0.8%。调试结果验证了0.6m连续式跨声速风洞设计方案的可行性，为我国大型连续式跨声速风洞研制提供参考。Abstract: The 0.6m continuous transonic wind tunnel of CARDC, a circling wind tunnel, use dry air in variable density as working medium. The major components of the wind tunnel include broad-performance compressor, semi-flexible nozzle, lower-noise test section, re-entry flaps and slots, heat-exchange system and the second throat with wall flaps and center body. In order to get the general performance and the secure running boundary of the wind tunnel, the general performance calibration is carried out. Calibration results indicate that the general performances and each section of the wind tunnel agree well with the requirements. The compressor, heat-exchange system and other auxiliary equipments are all in working order. The range of total pressure in settling chamber is 15~250kPa and the control precision of the total pressure is better than 0.2%. The Mach number in the test section is in the range of 0.144~1.640 and the control precision of the Mach number is better than 0.002. The flow qualities such as the fluctuation of Mach number distribution have met the requirements(Ma ≤ 1.0, σMa < 0.002;1.0 < Ma ≤ 1.6, σMa < 0.008). When the Mach number is greater than 0.5, the flow fluctuation coefficient which is used to represent the noise level is below 0.8%. The design scheme's feasibility of the 0.6m continuous transonic wind tunnel is fully verified by the debugging results, which provide scientific guidance for the development of the large-scale continuous transonic wind tunnel.
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图 2 主压缩机测试性能曲线(静叶角66°)
Figure 2. Performance curves of the main compressor (static vane angle at 66°)
图 4 不同总压状态马赫数控制精度
Figure 4. Control precision of Ma under different operation pressures
图 5 槽壁试验段轴向马赫数分布
Figure 5. Axial distribution of Ma in test section with slotted walls
表 1 风洞总体性能参数实测值与设计要求比较
Table 1. Comparison of measured and required general performance of the wind tunnel
项目 性能要求 实测值 Ma 0.20~1.60 0.15~1.64 总压/Pa (0.15~2.50)×105 (0.15~2.50)×105 总温/K 273~323 280~310 Re (0.1~2.25)×106 (0.1~2.25)×106 主压缩机轴功率/MW N≤3.80 N≤3.75 辅压缩机轴功率/MW N≤1.50 N≤1.20 风洞试验时间 可连续运行(额定2h) 可连续运行(8h) 
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表 2 四壁孔壁试验段纵向气流偏角测量结果
Table 2. The vertical average flow angles in test section with perforated walls
Ma 0.20 0.30 0.40 0.50 0.60 0.70 0.80 0.90 Δα/(°) 0.063 0.016 0.029 0.054 0.016 0.022 0.003 0.005 Ma 0.95 1.00 1.05 1.10 1.15 1.20 1.30 1.40 Δα/(°) 0.027 0.062 0.081 0.012 0.026 0.045 0.035 0.069
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表 3 风洞超声速流场实测结果
Table 3. Measurement results of supersonic flow quality
Ma=1.4 Ma=1.5 Ma=1.6 最大Ma偏差 0.00652 0.00886 0.01107 Ma均方根偏差 0.00288 0.00348 0.00427 Ma轴向静压梯度/m-1 -0.00281 -0.00274 -0.00182
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