双爆轰管脉冲爆轰发动机近场噪声特性的试验研究  

Experimental Study on Acoustic Behavior of Dual-Tube Pulse Detonation Engine in Near Field

作　　者：黄孝龙[1] 翁春生[1] 李宁[1] 许桂阳 

机构地区：[1]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《推进技术》2017年第5期1194-1200,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金项目(11472138);中央高校基本科研业务专项资金资助(30920130112007);国防预研基金(9140c300202120c30)

摘　　要：为研究双管脉冲爆轰发动机近场爆轰噪声特性,设计了双管脉冲爆轰发动机爆轰噪声试验测试系统,对不同填充率、不同管间距下的爆轰噪声进行了测量。试验结果表明:随着传播距离的增加,爆轰噪声峰值声压逐渐减小。PDE管口附近,爆轰噪声峰值声压衰减速度最快;距离管口较远位置处,衰减速度逐渐减小。随着填充系数的增加,爆轰噪声逐渐增大,指向性逐渐变缓;距离管口400mm处,60%,100%和140%填充系数下峰值声压级依次为197.95,201.93和204.51d B。不同传播距离处,爆轰噪声指向性不同。当距离管口较近时,爆轰噪声最大值出现在0°方向;距离管口大于2m的区域内,最大值出现在30°方向。不同管间距情况下,爆轰噪声呈现出相同的指向性。管间距越小,爆轰噪声的指向性越明显。The experiment system with dual-tube pulse detonation engine is designed to investigate the noise characteristic of dual-tube pulse detonation engine with different filling fractions and different detonation tube separation distances. The experimental results show that as the propagation distance increases,the detonation peak pressure decreases quickly and its decay rate reaches the highest around PDE exit. The decay rate slows down in the region of far from tube exit. With the increase of filling fraction,the detonation noise pressure increases and the detonation noise directivity slows down gradually. At the location of 400 mm away from tube exit,the peak sound pressure level is 197.95 d B,201.93 d B and 204.51 d B under the condition of 60%,100% and140% filling fraction,respectively. At different propagation distance,the directivity changes. The highest detonation noise pressure appears in 0° direction around PDE exit and it appears in 30° direction in the region of more than 2m away from tube exit. The detonation noise shows the same directivity at different detonation tube separation distances and the directivity appears more obviously with separation distance decreases.

关 键 词：脉冲爆轰发动机 爆轰噪声 填充系数 指向性 管间距 声压级 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]