直升机涵道尾桨气动噪声特性风洞试验研究

丁存伟; 周国成; 陈宝; 仲唯贵

doi:10.11729/syltlx20210186

直升机涵道尾桨气动噪声特性风洞试验研究

丁存伟^{1, 2, 3, ,},
周国成^{1, 2, 3},
陈宝^{1, 2, 3},
仲唯贵⁴

1.
中国航空工业空气动力研究院，哈尔滨　150001
2.
黑龙江省空气动力噪声及其控制重点实验室，哈尔滨　150001
3.
低速高雷诺数气动力航空科技重点实验室，哈尔滨　150001
4.
中国直升机设计研究所，景德镇　333000

详细信息

作者简介:
丁存伟: （1987—），男，黑龙江齐齐哈尔人，高级工程师。研究方向：航空声学设计和试验技术。通信地址：黑龙江省哈尔滨市平房区祥云路6号（150001）。E-mail：dingcunwei@126.com

通讯作者:
丁存伟: E-mail：dingcunwei@126.com

中图分类号: V211.7
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出版历程
- 收稿日期: 2021-12-14
- 修回日期: 2022-01-16
- 录用日期: 2022-01-28
- 刊出日期: 2023-06-24

Experimental study on aerodynamic noise characteristics of helicopter ducted tail rotor

DING Cunwei^{1, 2, 3, ,},
ZHOU Guocheng^{1, 2, 3},
CHEN Bao^{1, 2, 3},
ZHONG Weigui⁴

1.
AVIC Aerodynamics Research Institute, Harbin　150001, China
2.
Heilongjiang Provincial Laboratory of Aerodynamic Noise and Control , Harbin　150001, China
3.
Aviation Key Laboratory of Aerodynamics for Low Speed and High Reynolds Number, Harbin　150001, China
4.
China Helicopter Research and Development Institute, Jingdezhen　333000, China

摘要

摘要: 基于中国航空工业空气动力研究院FL–52航空声学风洞试验条件，对直升机涵道尾桨模型的气动噪声特性进行了试验研究。对试验数据进行了射流剪切层影响修正，获得了涵道尾桨在悬停、前飞状态下的噪声频谱及远场指向性。分析了噪声随桨尖马赫数的变化规律，结果显示涵道尾桨气动噪声符合载荷噪声特性。对比了桨叶沿桨毂周向分布规律对气动噪声频谱特征的影响。获得了悬停和前飞状态下涵道对噪声传播的遮蔽效果影响，悬停状态下尾桨旋转平面内噪声降低约2 dB，前飞状态下尾桨旋转平面内噪声降低5～8 dB。
- 涵道尾桨 /
- 气动噪声 /
- 声学风洞 /
- 直升机
Abstract: Using the FL–52 aero-acoustic wind tunnel test system of the Aerodynamics Research Institute, the experimental study on the ducted tail rotor noise characteristics is carried out. The influence of the jet shear layer on the test data is corrected, and the noise spectrum and far-field directivity of the culvert tail rotor in hover and forward flight are obtained. The variation laws of the noise with the Mach number of the tail rotor tip are analyzed, and the results show that the aerodynamic noise of the ducted tail rotor conforms to the load noise characteristics. The effects of the blade distribution along the hub on the spectral characteristics of the aerodynamic noise are compared. The shielding noise reduction effect of the duct on the noise propagation under typical working conditions is obtained in hover, the noise in the rotating plane is 2 dB lower than that in other positions in forward flight, the noise reduction in the rotating plane is 5 – 8 dB.
- ducted tail rotor /
- aerodynamic noise /
- aero-acoustic wind tunnel /
- helicopter

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图 1 尾桨试验模型

Fig. 1 Test models of ducted tail rotor

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图 2 风洞内涵道尾桨试验系统

Fig. 2 Ducted tail rotor test system in aero-acoustic wind tunnel

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图 3 远场测点布置示意图

Fig. 3 Diagram of noise measurement points

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图 4 射流剪切层构建Snell定律

Fig. 4 Scheme of Snell law in the shear-layer

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图 5 尾桨模型Rotor1总距25°噪声频谱

Fig. 5 Noise spectrum of Rotor1 at total pitch angle of 25°

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图 6 尾桨模型Rotor2总距25°噪声频谱

Fig. 6 Noise spectrum of Rotor2 at total pitch angle of 25°

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图 7 尾桨模型Rotor1总距20°噪声频谱

Fig. 7 Noise spectrum of Rotor1 at total pitch angle of 20°

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图 8 悬停状态下涵道尾桨噪声指向性

Fig. 8 Directivity of ducted tail rotor noise in hover state

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图 9 前飞状态下的噪声指向性

Fig. 9 Directivity of ducted tail rotor noise in forward flight

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图 10 尾桨模型Rotor1前飞状态噪声频谱

Fig. 10 Noise spectrum of Rotor1 in forward flight

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图 11 尾桨模型Rotor2前飞状态噪声频谱

Fig. 11 Noise spectrum of Rotor2 in forward flight

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表 1 FL–52风洞性能参数

Table 1 The performance parameters of FL–52 wind tunnel

参数	值
开/闭口试验段截面尺寸	2 m（宽） × 1.5 m（高） × 6.3 m（长）
试验段长度	6.3 m
开口试验段最大风速	100 m/s
闭口试验段最大风速	110 m/s
消声室尺寸	16 m（宽） × 11.5 m（高） × 15.5 m（长）
背景噪声	< 74.6 dB（A）（开口试验段最大风速80 m/s时）

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表 2 试验模型主要参数

Table 2 Experimental model parameters

参数	值
桨叶直径	0.667 m
桨叶数目	10 片
桨毂直径	0.27 m
桨尖与涵道间隙	3 mm

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表 3 来流风速30 m/s下剪切层修正角度

Table 3 Correction results of jet shear layer at the velocity of 30 m/s

麦克风	修正前角度	修正后角度	修正量
R1	80°	80.43°	0.43°
R2	90°	90.36°	0.36°
R3	100°	100.28°	0.28°
R4	110°	110.18°	0.18°
R5	120°	120.12°	0.12°
R6	130°	130.07°	0.07°
R7	180°	180.00°	0°

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表 4 2种试验模型悬停状态典型频率对比

Table 4 Typical frequency of two test models in hover

频率/Hz	声压级/dB
频率/Hz	Rotor1	Rotor2
100	55.5	61.7
300	46.2	67.4
400	54.9	66.5
500	70.9	61.3
600	44.6	69.4
1000	65.2	48.5
1500	61.5	51.5

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参考文献(15)

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