Full-Text Search:
Home|Journal Papers|About CNKI|User Service|FAQ|Contact Us|中文
《防务技术(英文版)》 2013-03
Add to Favorite Get Latest Update

Numerical Research on The Nozzle Damping Effect by A Wave Attenuation Method

Wan-xing SU;Ning-fei WANG;Jun-wei LI;Yan-dong ZHAO;Mi YAN;School of Aerospace Engineering,Beijing Institute of Technology;  
Nozzle damping is one of the most important factors in the suppression of combustion instability in solid rocket motors.For an engineering solid rocket motor that experiences combustion instability at the end of burning,a wave attenuation method is proposed to assess the nozzle damping characteristics numerically.In this method,a periodic pressure oscillation signal which frequency equals to the first acoustic mode is superimposed on a steady flow at the head end of the chamber.When the pressure oscillation is turned off.the decay rate of the pressure can be used to determine the nozzle attenuation constant.The damping characteristics of three other nozzle geometries are numerically studied with this method under the same operating condition.The results show that the convex nozzle provides more damping than the conical nozzle which in turn provides more damping than the concave nozzle.All the three nozzles have better damping effect than that of basic nozzle geometry.At last.the phase difference in the chamber is analyzed,and the numerical pressure distribution satisfies well with theoretical distribution.
【CateGory Index】: V431
Download(CAJ format) Download(PDF format)
CAJViewer7.0 supports all the CNKI file formats; AdobeReader only supports the PDF format.
©2006 Tsinghua Tongfang Knowledge Network Technology Co., Ltd.(Beijing)(TTKN) All rights reserved