对转螺旋桨气动噪声试验系统设计与试验研究  

Aeroacoustic test system design and experimental research for counter-rotating propeller

作　　者：曹琦[1] 卫凯 聂彦平 燕群[1] 陈永辉[1] CAO Qi;WEI Kai;NIE Yanping;YAN Qun;CHEN Yonghui(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China;Design and Research Institute,AVIC Shaanxi Aircraft Industry Co.,Ltd.,Hanzhong 723000,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710065 [2]航空工业陕西飞机工业(集团)有限公司设计研究院,汉中723000

出　　处：《航空工程进展》2024年第5期148-154,共7页Advances in Aeronautical Science and Engineering

基　　金：中国飞机强度研究所创新基金项目(BYSFMJKY-18-024)。

摘　　要：风洞内对转螺旋桨气动噪声试验存在时间协调难、成本高的问题,依托地面声学环境,研制能够模拟对转螺旋桨地面开车状态的对转螺旋桨气动噪声试验系统。对某穿孔结构的对转螺旋桨和基准桨开展气动噪声试验,对设计的试验系统进行验证,并对穿孔结构对转螺旋桨的降噪效果进行评估。结果表明:在所测试的工况范围内,穿孔结构对转螺旋桨在保证气动性能的前提下能够有效降低噪声;在对飞机舱内影响最显著的90°指向角处,二阶通过频率处降噪量达到5 dB。本文设计的气动噪声试验系统,能够为对转螺旋桨气动噪声评估和降噪设计提供帮助。The aerodynamic noise test of counter-rotating propellers in wind tunnels has the problems of difficult time coordination and high cost.The aerodynamic noise test system of counter-rotating propellers,which is capable of simulating the driving state of counter-rotating propellers on the ground,is developed by relying on the acoustic environment of the ground.The aerodynamic noise test is carried out on a perforated counter-rotating propeller and a reference propeller to validate the test system and evaluate the noise reduction effect of the perforated counter-ro-tating propeller.The results show that the perforated counter-rotating propeller can effectively reduce the noise un-der the prerequisite of guaranteeing the aerodynamic performance in the range of the tested working conditions.In the 90°pointing angle,which has the most significant effect on the aircraft cabin,the noise reduction at the second-order passing frequency reaches 5 dB.The designed aerodynamic noise test system can provide assistance for the evaluation of aerodynamic noise of the counter-rotating propeller and the design of noise reduction.

关 键 词：对转螺旋桨 气动噪声 穿孔结构 远场噪声 降噪设计 

分 类 号：V211.44[航空宇航科学与技术—航空宇航推进理论与工程] V216.54