Design and actualization of the variable density plane cascade wind tunnel
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摘要: 为满足先进涡扇发动机对变雷诺数平面叶栅试验的需求，设计了亚/跨/超声速来流高效变换、雷诺数和马赫数独立调节、压气机和涡轮平面叶栅试验为一体、换热与冷却试验能力兼具的变密度平面叶栅风洞，提出了风洞的总体设计方案。文章详细介绍了风洞引射器、半柔壁喷管及试验舱等部件设计问题，分析了流场调试及典型叶栅试验结果。调试结果表明：采用的部件设计技术实现了变密度平面叶栅风洞的主要功能，试验雷诺数可低至3.1×105 m–1，具备开展低雷诺数平面叶栅试验的能力。风洞流场调试结果满足《低速风洞和高速风洞流场品质要求》（GJB 1179A—2012），为研究亚/跨/超声速压气机和涡轮叶栅低雷诺数流动问题提供了重要试验平台。Abstract: In order to meet the need of the variable Reynolds number plane cascade tests for the advanced turbofan engine, the variable density plane cascade wind tunnel was designed to change the subsonic, transonic and supersonic flow efficiently, adjust the Mach number （Ma） and Reynolds number （Re） independently, combine the compressor and turbine cascade tests and possess the ability of heat transfer or cooling experiments. The general design project of the wind tunnel was put forward, and the ejector, the flexible nozzle as well as the test chamber design problems were introduced in details. The results of the flow field debugging and the typical cascade tests were analysed. The research reveals that the design technologies of the components satisfy the main functions of the variable density plane cascade wind tunnel. The Reynolds number can be as low as 3.1×105 m–1 so that the low Reynolds number experiments can be made easyly with the facility. The flow field debugging results satisfy the National military standard GJB 1179A—2012 of the specification for flow quality of high and low speed wind tunnels. It provides a key test platform for the study of the transonic, supersonic Mach number and low Reynolds number flow problems of the compressor and turbine cascades.
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Keywords:
- plane cascade /
- wind tunnel /
- turbomachinery /
- Reynolds number /
- Mach number
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图 8 试验段不同宽度位置流场马赫数分布（Ma=0.8）
Fig. 8 Flow field mach number distributions in different width positions
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图 9 不同宽度位置流场气流角分布（Ma=0.8）
Fig. 9 Flow field flow angle distributions in different width positions
表 1 风洞主要技术参数
Table 1 Main technical parameters of the wind tunnel
序号 参 数 数 值 1 试验段截面尺寸 190 mm×445 mm 2 试验马赫数 0.3～1.8 3 试验雷诺数 3.1×105～4.5×107 m−1 4 次流温度 170～373 K 5 稳定段总压 5～300 kPa 6 稳定段总温 常温 7 叶片数 ≥7 8 典型弦长 75～120 mm 9 气流角调节范围 0°～180° 
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表 2 三级引射器主要技术参数
Table 2 Main technical parameters of the three stages injector
级号 py/MPa m/（kg﹒s–1） May pb/kPa 1 0.25 3.96 3.6 93.6 2 0.36 16.38 3.0 80.0 3 0.96 79.60 2.8 20.0
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