集束氧槍環流布置模式對射流流場影響規律研究

劉福海; 姚柳潔; 馬浩冉

doi:10.13374/j.issn2095-9389.2018.s1.017

集束氧槍環流布置模式對射流流場影響規律研究

doi: 10.13374/j.issn2095-9389.2018.s1.017

劉福海^1,2,
姚柳潔^2,3,
馬浩冉^2,3, ,

1. 北京科技大學國家材料服役安全科學中心;
2. 北京科技大學高端金屬材料特種熔煉與制備北京市重點實驗室;
3. 北京科技大學冶金與生態工程學院

基金項目:

中央高校基本科研專項資金資助項目 (FRF-AS-17-005)

中國博士后科學基金資助項目 (2017M620614)

“十二五”國家科技支撐計劃重點資助項目 (2017M620614)

詳細信息

通訊作者:
馬浩冉, E-mail:mahaoranustb@163.com

中圖分類號: TF701
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- 文章訪問數: 21
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- 被引次數: 0
出版歷程
- 收稿日期: 2018-02-05
- 網絡出版日期: 2023-07-18

Effect of shrouding nozzle arrangement on the flow field characteristics of coherent jet

LIU Fu-hai^1,2,
YAO Liu-jie^2,3,
MA Hao-ran^{2,3
, ,}

1. National Center for Materials Service Safety,University of Science and Technology Beijing;
2. Beijing Key Laboratory of Research Center of Special Melting and Preparation of High-end Metal Materials,University of Science and Technology Beijing;
3. School of Metallurgical and Ecological Engineering,University of Science and Technology Beijing

摘要

摘要: 為進一步提高集束氧槍對熔池的沖擊攪拌效果, 重點分析了在兩種環境下, 不同環流布置模式對超音速氧氣射流流場與沖擊能力的作用效果.通過對比在高溫噴射試驗與數值模擬研究結果, 分析射流軸向速度與射流總溫流動狀態, 研究不同環流布置模式下集束射流沖擊特性.通過分析不同數量網格的可靠性, 選取合適的數值模擬模型, 并采用渦耗散概念模型和多步燃燒反應機理計算超音速狀態下氧氣與甲烷的混合與燃燒過程.研究結果表明數值模擬結果與高溫噴射試驗數據吻合程度較好.環流布置對拉瓦爾管出口流速無明顯影響, 主氧射流核心段隨環流孔徑與主氧射流間距的增大, 有先提高后下降的趨勢, 且不同環流布置模式對主氧核心段均有延長效果.
- 超音速射流 /
- 集束射流 /
- 燃燒試驗 /
- 數值模擬
Abstract: The coherent lance technology is widely used in the electric arc furnace (EAF) steelmaking process.It achieves a better metallurgical effect compared with the conventional supersonic lance technology.Herein, to further improve the stirring ability of the coherent lance, the effects of shrouding nozzle arrangement on the flow field and stirring ability of coherent jet were analyzed under two environment temperatures.Based on the results of the numerical simulation and combustion experiment, the characteristics of axial velocity and total temperature distributions has been introduced for researching the impaction ability of coherent jet using various shrouding nozzle arrangements.The appropriate simulation model was built by testing three types of mesh levels.The eddy dissipation concept (EDC) model and chemical kinetic mechanism were adopted to represent the combustion reactions of the O₂-CH₄jet flame in the numerical simulation process.Resultsreveals that the numerical simulation data shows good agreement with combustion experiment.The initial velocity at the exit of main oxygen Laval nozzle does not change with different shrouding nozzle arrangements.With increase in the distance between the main oxygen and shrouding nozzles, the length of the velocity potential core first increases and then reduces.Moreover, all shrouding nozzle arrangements increase the length of velocity potential core.
- supersonic jet /
- coherent jet /
- combustion experiment /
- numerical simulation

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參考文獻(15)

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