5.5 m×4 m航空声学风洞结构设计与研究

doi:10.7527/S1000-6893.2022.27711

Abstract

Abstract:

The 5.5 m × 4 m aeroacoustic wind tunnel， as the first large aeroacoustic wind tunnel in China， was put into use at 2015， which filled the gap in the field of ground test research platform on aircraft aeroacoustic in China. In this work. The overall structure design of wind tunnel and detailed structure design of main sections are carried out in consideration of the wind tunnel characteristics including test capability on aeroacoustic， fast switching between open test status and closed test status and adaptability of model support system to test requirements under multiple working condition. The wind tunnel loop is made up of the replaceable large steel structure and concrete structure， which satisfies the multifunctional layout requirements of aerodynamics-acoustics and opening-closing status. The integrally movable multifunctional abdominal support device driven by handspike and the deeply embedded long stroke liftable tail support mechanism with the advantage of high accuracy are employed to achieve the fast switching between open test status and closed test status. The spherical wheel hub， the spherical blade with the adjustable blade angle and the locking structure between the flange and apical petiole are adopted to reduce the aerodynamic noise of blade root as far as possible and to achieve the reliable operation of fan rotor， which can satisfy the requirement of low noise of fan in combination of noise reduction measures taken at the wall. The test results show the safe and reliable operation of wind tunnel structure and the high test efficiency， which proves the success of structure design of 5.5 m × 4 m aeroacoustic wind tunnel.

Key words: aeroacoustic wind tunnel, structure design, test section, abdominal support device, tail support mechanism, fan

CLC Number:

V211.74

Wenguo YANG, Rui WANG, Yongtao YIN, Wanhua CHEN. Structure design and research of 5.5 m×4 m aeroacoustic wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023, 44(12): 127711-127711.

Figures/Tables 22

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References 21

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风洞名称	试验段尺寸（宽/m×高/m）	试验段形式	最大风速/（m∙s^-1）	噪声/dB（A）
美国NASA Ames 40×80	24.2×12.1	闭口	154	86 （闭口， 51 m/s）
美国DIFWT8（双试验段）	4.15×2.54	3/4开口	67	75 （开口， 55 m/s）
德国IVK Stuttgart	5.8×3.87×9	3/4 开口	73.1	84 （开口， 67 m/s）
德国Audi	3.94×2.8	3/4开口	83.3	79 （开口， 83 m/s）
日本RTRI	3.0×2.5	3/4开口	111.1	75.6 （开口， 83 m/s）
德国FKFS声学风洞	5.8×3.87	3/4开口	80	65 （开口， 39 m/s）
荷兰-德国DNW-LLF	8×6	开口	85	80 （开口， 80 m/s）
中国同济大学汽车风洞	6.35×4.2	3/4开口	85	76 （开口， 50 m/s）

频率f/Hz	50	63	80	100
吸声系数	0.755	0.895	0.983	0.994
频率f/Hz	125	160	200	250
吸声系数	0.997	0.999	0.999	0.997

名称	测试项目	测试结果	指标要求
腹撑	迎角定位精度/（°）	±0.01	±0.02
腹撑	侧滑角定位精度/（°）	±0.01	±.02
尾撑	迎角定位精度/（°）	±0.016	±0.02
尾撑	侧滑角定位精度/（°）	±0.011	±0.02

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Structure design and research of 5.5 m×4 m aeroacoustic wind tunnel

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