南京理工大学学报（自然科学版）
南京理工大學學報（自然科學版）
남경리공대학학보（자연과학판）
JOURNAL OF NANJING UNIVERSITY OF SCIENCE AND TECHNOLOGY
2014年
6期
781-786
,共6页
爆炸力学%脉冲爆轰发动机%雾化汽油%噪声辐射%指向性%爆轰噪声%冲击噪声%射流噪声%衰减系数%轴向距离
爆炸力學%脈遲爆轟髮動機%霧化汽油%譟聲輻射%指嚮性%爆轟譟聲%遲擊譟聲%射流譟聲%衰減繫數%軸嚮距離
폭작역학%맥충폭굉발동궤%무화기유%조성복사%지향성%폭굉조성%충격조성%사류조성%쇠감계수%축향거리
explosion mechanics%pulse detonation engines%atomizing gasoline%noise radiation%directivity%detonation noise%impulsive noise%jet noise%attenuation coefficients%axial distance
为探索气液两相脉冲爆轰发动机爆轰噪声形成机理及控制方法，对雾化汽油近场爆轰噪声进行测量分析，建立理论模型并利用时空守恒元/求解元方法( CE/SE)进行数值仿真。结果表明：爆轰噪声主要由冲击噪声和射流噪声组成；冲击噪声在爆轰噪声中占主导作用，并引起爆轰噪声峰值；爆轰噪声峰值与径向距离三次方成反比；在0°、30°、45°和90°方向拟合得到的衰减系数分别为4.3×10-2、3.4×10-2、2.8×10-2和7.0×10-3；脉冲爆轰发动机近场爆轰噪声峰值指向性明显；随着角度的增大，爆轰噪声峰值逐渐降低；随着轴向距离的增加，射流噪声逐渐减小；当轴向距离小于900 mm时，射流噪声衰减速度小于冲击噪声衰减速度，当轴向距离大于1200 mm时，射流噪声衰减速度大于冲击噪声衰减速度。
為探索氣液兩相脈遲爆轟髮動機爆轟譟聲形成機理及控製方法，對霧化汽油近場爆轟譟聲進行測量分析，建立理論模型併利用時空守恆元/求解元方法( CE/SE)進行數值倣真。結果錶明：爆轟譟聲主要由遲擊譟聲和射流譟聲組成；遲擊譟聲在爆轟譟聲中佔主導作用，併引起爆轟譟聲峰值；爆轟譟聲峰值與徑嚮距離三次方成反比；在0°、30°、45°和90°方嚮擬閤得到的衰減繫數分彆為4.3×10-2、3.4×10-2、2.8×10-2和7.0×10-3；脈遲爆轟髮動機近場爆轟譟聲峰值指嚮性明顯；隨著角度的增大，爆轟譟聲峰值逐漸降低；隨著軸嚮距離的增加，射流譟聲逐漸減小；噹軸嚮距離小于900 mm時，射流譟聲衰減速度小于遲擊譟聲衰減速度，噹軸嚮距離大于1200 mm時，射流譟聲衰減速度大于遲擊譟聲衰減速度。
위탐색기액량상맥충폭굉발동궤폭굉조성형성궤리급공제방법，대무화기유근장폭굉조성진행측량분석，건립이론모형병이용시공수항원/구해원방법( CE/SE)진행수치방진。결과표명：폭굉조성주요유충격조성화사류조성조성；충격조성재폭굉조성중점주도작용，병인기폭굉조성봉치；폭굉조성봉치여경향거리삼차방성반비；재0°、30°、45°화90°방향의합득도적쇠감계수분별위4.3×10-2、3.4×10-2、2.8×10-2화7.0×10-3；맥충폭굉발동궤근장폭굉조성봉치지향성명현；수착각도적증대，폭굉조성봉치축점강저；수착축향거리적증가，사류조성축점감소；당축향거리소우900 mm시，사류조성쇠감속도소우충격조성쇠감속도，당축향거리대우1200 mm시，사류조성쇠감속도대우충격조성쇠감속도。
To study the formation mechanism and control method of detonation noise for gas-liquid two-phase pulse detonation engines,atomizing gasoline detonation noise in near-field is measured and analyzed. A theory model is set up and the space-time conservation element and solution element method( CE/SE) is utilized in near-field numerical simulation of pulse detonation engine detonation noise. The results show that:detonation noise is mainly composed of impulsive noise and jet noise;impulsive noise plays a dominant role in detonation noise and causes detonation peak noise;detonation peak noise is proportional to -3 power of the radial distance in near-field;the fitted attenuation coefficients are 4. 3×10-2,3. 4×10-2,2. 8×10-2 and 7. 0×10-3 at the 0°,30°,45° and 90 ° directions;obvious directivity of pulse detonation engine detonation peak noise occurs in near-field;pulse detonation engine detonation peak noise amplitude decrease gradually with the increase of measurement angle;pulse detonation engine jet noise amplitude decrease gradually with the increase of axial distance;when the axial distance is less than 900mm,the rate of jet noise decay is lower than that of the impulsive noise;when the axial distance is more than 1 200 mm, the rate of jet noise decay is higher than that of the impulsive noise.
