安装效应对螺旋桨纯音噪声的影响

周家检; 郝璇; 徐琛

doi:10.7638/kqdlxxb-2024.0158

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安装效应对螺旋桨纯音噪声的影响

研究论文 | 更新时间：2026-05-28

- 安装效应对螺旋桨纯音噪声的影响
- Installation effects on propeller tone noise
- 空气动力学学报 2026年44卷第4期页码：54-64
- 作者机构：
  
  1. 中国航天空气动力技术研究院空气动力研究所,北京,100074
  2. 中国空气动力研究与发展中心气动噪声控制重点实验室,绵阳,621000
  3. 北京航空航天大学航空发动机研究院,北京,102206
  4. 中国航发商用航空发动机有限责任公司测试技术部,上海,200241
- 作者简介：
  
  周家检（1985—），男，江西萍乡人，高级工程师，研究方向：气动噪声测试技术. E-mail：zhoujjbuaa@qq.com
  郝璇*，研究员，研究方向：气动优化与气动噪声研究. E-mail：haoxuancaaa@163.com
- 基金信息：
  
  气动噪声控制重点实验室研究基金（ANCL20200201）;国家自然科学基金叶企孙基金（U2241271）
- DOI：10.7638/kqdlxxb-2024.0158
  中图分类号： O422.2
- 纸质出版：2026
- 稿件说明：
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周家检, 郝璇, 徐琛. 安装效应对螺旋桨纯音噪声的影响[J]. 空气动力学学报, 2026, 44(4): 54−64.

Zhou Jiajian, Hao Xuan, Xu Chen. Installation effects on propeller tone noise[J]. 2026, 44(4): 54-64.
周家检, 郝璇, 徐琛. 安装效应对螺旋桨纯音噪声的影响[J]. 空气动力学学报, 2026, 44(4): 54−64. DOI： 10.7638/kqdlxxb-2024.0158

Zhou Jiajian, Hao Xuan, Xu Chen. Installation effects on propeller tone noise[J]. 2026, 44(4): 54-64. DOI： 10.7638/kqdlxxb-2024.0158.

摘要

安装效应对螺旋桨噪声特性有显著影响。本文以简化机翼-螺旋桨模型为研究对象，针对起飞工况，采用非定常数值模拟手段，获得了不同安装位置总噪声特性、部件噪声特性以及关键流场特征，分析了安装效应对螺旋桨纯音噪声产生及传播特性的影响。结果表明，安装效应使螺旋桨推力增大、最大纯音噪声增加、远场最大噪声方向朝上游移动。桨盘与机翼重合的区域是尾流干扰影响区域，尾流-机翼干扰噪声水平受马赫数、尾流涡量和扫掠范围等因素影响。当机翼前缘位于桨盘平面水平距离

= 0.5

、垂直距离

0.3

区域时，此种安装位置不仅能够明显降低安装效应影响，同时还可使螺旋桨推力增加1%。本研究明确了安装位置对螺旋桨纯音噪声的影响规律，可为螺旋桨飞机动力装置的低噪声布局设计提供参考。

Abstract

The installation effects impose a distinct influence on the propeller noise characteristics. A simplified wing-propeller model with diverse installation positions were studied using unsteady numerical simulations to obtain the overall noise characteristics

component noise characteristics and key flow features under the take-off condition. The influence of installation locations on the propeller tone noise generation and radiation were analyzed. The results show that the installation effects lead to an increase of the thrust and maximum tone noise

and the direction of maximum tone noise moved upstream. The overlaid area between the propeller and the wing is the

main region of wake-wing interaction

where the noise level is affected by Mach number

wake vorticity

wake-sweep region and so on. When the leading edge of the wing lies in the region with a horizontal distance of

= 0.5

and a vertical distance of

0.3

the installation effects can be weakened dramatically while the thrust can be still increased by 1%. The patterns of installation effect on propeller tone noise are identified from this research

which can be referred for low noise design of prop airplane.

关键词

Keywords

references

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