0.6m连续式风洞调试运行关键技术研究

熊波; 周恩民; 程松; 张文; 刘恺; 罗新福

doi:10.11729/syltlx20150052

0.6m连续式风洞调试运行关键技术研究

中国空气动力研究与发展中心高速空气动力研究所, 四川绵阳 621000

详细信息

通讯作者:
熊波(1980-),男,四川眉山人,工程师。研究方向:高速风洞性能调试及优化。通信地址:四川绵阳211信箱2分箱(621000)。E-mail:6643807@qq.com

中图分类号: V211.74
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出版历程
- 收稿日期: 2015-04-05
- 修回日期: 2015-11-30
- 刊出日期: 2016-08-24

Research on key technologies of debugging and operating in 0.6m×0.6m continuous transonic wind tunnel

High Speed Aerodynamics Research Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

摘要

摘要: 为了降低大型连续式风洞建设风险，在0.6m连续式风洞中开展了压缩机防喘振控制、转速控制、马赫数控制等调试运行关键技术研究。本研究采用压力波动法准确测量出了压缩机的喘振边界，通过设置合理的报警线和防喘振线，保证了压缩机的安全；采用矢量控制技术实现了转速的精确控制，控制精度达到0.03%的设计要求；采用压缩机转速、驻抽流量以及中心体开度与马赫数的函数关系，实现了马赫数的精确控制，控制精度达到了0.002的设计指标要求。通过研究各项关键技术实现了该风洞定总压、定马赫数的运行方式，该风洞具有优良的流场品质，是开展基础研究平台建设和大型连续式风洞引导性研究的理想平台。
- 连续式风洞 /
- 调试 /
- 压缩机 /
- 流场 /
- 控制精度
Abstract: In order to reduce the risk of constructing a large-scale continuous wind tunnel, research on key technologies is carried out in the 0.6m wind tunnel of China Aerodynamics Research and Development Center, such as anti surge control and speed control of the compressor, Mach number control, and so on. Pressure fluctuation method is used to measure the surge margin of the compressor accurately, and the security of the compressor can be well ensured by setting a reasonable alarm line and surge line. Vector control technology is used to achieve the accurate control of speed, and the 0.03% control precision is achieved. The accurate control of Mach number is achieved by the function relationship between the compressor speed, chamber flow, the centrosome displacement and the Mach number, and the 0.002 control precision is achieved. Through the research of the key technologies, the operation mode of fixing stagnation pressure and Mach number is realized. Due to the excellent quality of flow fields achieved in the wind tunnel, it is a good platform to carry out basic and leading research on the construction of large continuous wind tunnels.
- continuous wind tunnel /
- debugging /
- compressor /
- flow field /
- control precision

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图 1 0.6m连续式风洞轮廓图

Fig. 1 Sketch of the 0.6m continuous wind tunnel

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图 2 喘振边界线测试结果(θ=66°，p₀=100kPa)

Fig. 2 Surge margin test result(θ=66°,p₀=100kPa)

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图 3 防喘振曲线设置(θ=66°)

Fig. 3 Anti-surge curve setting(θ=66°)

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图 4 防喘振控制逻辑框图

Fig. 4 Anti-surge control logic

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图 5 矢量控制拓扑图

Fig. 5 The vector control topology

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图 6 转速控制精度测试原理图

Fig. 6 Schematic diagram of the rotation measurement system

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图 7 转速与总压特性曲线

Fig. 7 Curves of rotating speed and stagnation pressure

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图 8 稳转速状态下，转速与总压特性曲线

Fig. 8 Rotating speed and stagnation pressure characteristic curves of steady state

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图 9 转速与马赫数特性曲线

Fig. 9 Curves of rotating speed vs. Mach number

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图 10 中心体开度与马赫数特性曲线

Fig. 10 Curves of Mach number vs. opening of centrosome

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图 11 驻抽流量与马赫数的关系曲线

Fig. 11 Curves of mass ratio vs. Mach number

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图 12 总压控制策略试验结果

Fig. 12 Results of stagnation pressure control strategy

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图 13 马赫数策略调试结果

Fig. 13 Results of Mach number control strategy

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表 1 转速控制精度测试结果

Table 1 Test result of the rotation control precision

转速/(r·min^-1)	最大转速/(r·min^-1)	最小转速/(r·min^-1)	控制精度/%
1500	1500.61	1499.63	0.0136
1800	1800.54	1799.8	0.0103
2400	2400.88	2399.17	0.0238
3000	3000.73	2999.51	0.0169
3600	3601.2	3599.12	0.0289

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表 2 辅压缩机转速对能耗的影响

Table 2 The effect of the assistant compressor’s rotation on energy consumption

Ma	流量阀开度	主机转速/(r·min^-1)	主机功率/kW	辅机转速/(r·min^-1)	辅机功率/kW	总功率/kW
1	1	2765	2060	6150	505	2565
1	1	2729	1960	8571	1000	2960

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