旋转桨叶表面压力反演试验

卫凯; 徐琛; 燕群; 徐健; 王龙

doi:10.13224/j.cnki.jasp.20220645

旋转桨叶表面压力反演试验

doi: 10.13224/j.cnki.jasp.20220645

卫凯¹,
徐琛²,
燕群¹,
徐健¹,
王龙¹

1.
中国航空工业集团有限公司中国飞机强度研究所航空声学与振动航空科技重点实验室，西安 710065
2.
北京航空航天大学能源与动力工程学院，北京 100191

基金项目: 工业和信息化部资助项目（MJZ-2016-F-11）

详细信息

作者简介:
卫凯（1990-），男，工程师，硕士，主要从事航空发动机噪声控制研究

中图分类号: V231.3
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- 文章访问数: 108
- HTML浏览量: 42
- PDF量: 50
- 被引次数: 0
出版历程
- 收稿日期: 2022-08-31
- 网络出版日期: 2023-02-21

Inversion test of rotating blade surface pressure

1.
Aviation Technology Key Laboratory of Aeroacoustic and Virbration， Aircraft Strength Research Institute of China， Aviation Industry Corporation of China，Limited，Xi’an 710065，China
2.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China

摘要

摘要:
为了验证旋转桨叶表面压力的反演计算方法，搭建了旋转桨叶表面压力反演试验平台，对一套二叶螺旋桨的表面压力开展了反演试验。通过传声器阵列测量螺旋桨的远场噪声，利用Kulite压力传感器和离线式采集器测量桨叶表面的静压，并与计算结果进行对比。结果表明：在所研究的工况范围内，计算结果与试验结果吻合较好，趋势基本一致；其中两个测点的试验结果与计算结果误差在1%以内，精度很高；另两个测点的对比差值较大，主要是压力传感器安装工艺误差所导致的。
- 旋转桨叶 /
- 表面压力 /
- 压力反演 /
- 远场噪声 /
- 试验测量
Abstract:
In order to verify the inversion calculation method of the surface pressure of the rotating blade, an inversion test platform for the surface pressure of the rotating blade was built, and the inversion test for the surface pressure of a set of two-blade propellers was carried out. The far-field noise of the propeller was measured by a microphone array, and the static pressure on the blade surface was measured by a Kulite pressure sensor and an offline collector, and then compared with the calculated results. The results showed that under the working conditions studied, the calculated results were in good agreement with the experimental results, and the trend was basically the same; the error between the experimental results and the calculated results of two measuring points was within 1%, and the accuracy was very high; the contrast difference between the points was large, which was mainly caused by the installation process error of the pressure sensor.
- rotating blade /
- surface pressure /
- pressure inversion /
- far-field noise /
- test measurement

HTML

图 1 试验现场照

Figure 1. Test site photo

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图 2 反演桨转接盘局部照

Figure 2. Photo of adapter for inversion propeller

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图 3 传声器阵列空间布局示意图

Figure 3. Schematic diagram of microphone array layout

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图 4 桨叶表面压力测点位置示意图

Figure 4. Schematic diagram of position of pressure measurement points on blade

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图 5 2000 r/min远场噪声频谱

Figure 5. Spectra of far-field noise with 2000 r/min

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图 6 2000 r/min 1#传声器的噪声时频分布

Figure 6. Time-frequency distribution of 1# microphone with 2000 r/min

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图 7 2000 r/min桨叶表面压力计算结果与试验结果对比

Figure 7. Comparison of calculation results and test results of blade surface pressure with 2000 r/min

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图 8 2350 r/min桨叶表面压力计算结果与试验结果对比

Figure 8. Comparison of calculation results and test results of blade surface pressure with 2350 r/min

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表 1 2000 r/min桨叶表面压力计算结果与试验结果数据

Table 1. Data of calculation results and test results of blade surface pressure with 2000 r/min

测点表面压力/kPa 误差/%
试验结果计算结果

1# 102.106 101.013 1.07
2# 101.068 101.185 0.12
3# 100.285 101.589 1.3
4# 106.371 105.936 0.41

下载: 导出CSV

表 2 2350 r/min桨叶表面压力计算结果与试验结果数据

Table 2. Data of calculation results and test results of blade surface pressure with 2350 r/min

测点表面压力/kPa 误差/%
试验结果计算结果

1# 102.005 100.115 1.85
2# 100.349 100.321 0.02
3# 99.258 100.897 1.65
4# 106.065 106.826 0.22

下载: 导出CSV

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