压气机叶片气流流动发声机理的初步试验研究  

Experimental Investigation of the Sound Generated from the Compressor Blade Airflow

作　　者：尹红顺[1] 王永明[2] 余华蔚[1] 姜正礼[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500 [2]贵州航空发动机研究所,贵州贵阳550081

出　　处：《燃气涡轮试验与研究》2013年第4期1-7,共7页Gas Turbine Experiment and Research

摘　　要：以平面叶栅为试验研究对象,研究了叶片槽道气流旋涡与噪声声压级的关系。在此结果的基础上,以某发动机高压压气机零级静子叶片组成扇形试验件,在不同进口气流速度和攻角下,进行了叶片发声试验研究。得出了不同进口气流速度和攻角下,叶片出口气动噪声频谱及声压级的变化规律,认为分离区内强烈的气流脉动是其噪声产生的根源,且产生的较高能量的宽频噪声或宽频激振源会对构件产生声疲劳破坏,应引起足够重视并进行深入研究。Taking the compressor cascade as the testing research object, the relationship between the air-flow vortex of blade channels and the level of noise was investigated. On the basis of investigation results, zero-stage vanes of an aero-engine HPC were formed to sector test specimen and research on sound was carried out with different inlet airflow velocity and angle of attack. The vane outlet aerodynamic noise fre-quency spectrum and the level of noise varying with the inlet airflow velocity and angle of attack were ac-quired. It was recognized that strong airflow impulse in the separation zone was the cause of noise, at the same time the broadband noise or shock excitation source produced by airflow impulse would do acoustic fa-tigue to the construction parts that should arouse attention and deep research.

关 键 词：航空发动机 压气机 叶片发声机理 激振 气动声学试验 宽频噪声 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]