Characteristics and key technology analysis of large continuous transonic wind tunnel
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摘要: 大型连续式跨声速风洞具备飞行器外形精确模拟、气动弹性评估和机体/推进一体化设计等试验能力，试验段尺寸大、指标要求高、系统规模大、运行功能多。围绕大型连续式跨声速风洞的特点，简要介绍了大型连续式跨声速风洞总体设计方案，重点介绍了世界一流流场品质实现、大型轴流压缩机及其驱动系统研制等关键技术的初步研究成果。Abstract: The large scale continuous transonic wind tunnel has several main features, such as the large-size test section, high wind tunnel performance specifics, large scale wind tunnel system, multi-function wind tunnel operation. It has the test capabilities of accurate simulation of the aircraft shape, aero-elastic evaluation and integrated body/propulsion design. This paper briefly introduces the overall design of the large continuous transonic wind tunnel, and special focus is put on the preliminary research results of key technologies such as the realization of world-class flow quality and the development of the large axial compressor and its driving system.
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Key words:
- continuous wind tunnel /
- transonic wind tunnel /
- design /
- experimental investigations /
- key technology
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图 1 大型连续式跨超声速风洞气动总体布局示意图
Figure 1. Overall aerodynamic layout of large continuous transonic wind tunnel
图 3 常压状态下总压和马赫数控制精度
Figure 3. Control accuracy of total pressure and Mach number under atmospheric pressure
图 5 风洞回路降噪设计方案示意图
Figure 5. Schematic diagram of noise reduction design scheme for wind tunnel loop
图 6 板翅式热交换器试验件基本结构
Figure 6. Basic structure of plate-fin heat exchanger test specimen
表 1 大型连续式跨声速风洞和国内外风洞流场品质的比较
Table 1. Comparison of flow quality of the large continuous transonic wind tunnels in the world
指标 大型连续式跨声速风洞 2.4 m引射式跨声速风洞 欧洲跨声速风洞（ETW） 马赫数均匀性指标：σMa 0.001～0.002（Ma＜1.0）
0.004～0.008（Ma≥1.0）0.002～0.005（Ma＜1.0）
0.005～0.010（Ma≥1.0）0.001（Ma＜1.0）
0.008（Ma≥1.0）马赫数控制精度指标：ΔMa 0.001 0.002～0.003 0.001 气流偏角α 0.10°～0.20° 0.15° 0.10° 湍流度ε 0.05%～0.25% 0.05%（实测0.25%） 试验段噪声指标：ΔCp 0.6%～0.8%（Ma＜1.0） 1.6%～3.0% 0.6%（实测0.7%） 温度均匀性指标：ΔT0 1.0 K 0.5 K 
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