| 杨凯,唐丹娜,毕聪,王则皓,汤海斌.拉瓦尔喷管流固耦合换热效率研究[J].计算力学学报,2025,42(2):278~284 |
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| 拉瓦尔喷管流固耦合换热效率研究 |
| Study on heat transfer efficiency with fluid-solid coupling for Laval nozzle |
| 投稿时间：2023-09-16 修订日期：2023-11-29 |
| DOI：10.7511/jslx20230916007 |
| 中文关键词: 拉瓦尔喷管 冷却结构 螺旋型流道 |
| 英文关键词:Laval nozzle cooling design spiral channel |
| 基金项目:国家自然科学基金(52305382);机械结构力学及控制国家重点实验室基金(MCMS-E-0423Y01)资助项目. |
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| 中文摘要: |
| 开展热端部件冷却换热设计是提升航天发动机耐温性能的关键。面向发动机拉瓦尔喷管结构,本文基于计算流体力学,开展不同截面形貌(圆形、扇形、矩形)及不同螺旋排布(无螺旋、前置螺旋、全螺旋)的冷却流道组合设计研究,探索冷却换热设计新方式。数值仿真表明,相较于无冷却流道的尾喷管出口端面温度,含冷却流道的尾喷管出口端面温度存在明显下降;相比于圆形和扇形截面,矩形截面冷却流道的尾喷管冷却效率最高,出口端面平均温度下降达4.64%;螺旋型冷却流道的换热效率相比于常规流道有进一步提升,矩形截面螺旋设计的冷却流道方案出口端面的平均温度下降可达5.17%。研究结果可为航天发动机尾喷管冷却结构设计提供参考。 |
| 英文摘要: |
| The heat transfer design of hot end components is an efficient method to improve the temperature resistance for aerospace engines.Based on computational fluid dynamics,different shapes of the cross section(circular,fan-shaped,and rectangular) and different spiral distributions(straight,front helix,and full helix) are explored for the cooling channel within the Laval nozzles.The simulations results show that the temperature significantly decreases at the end face for the exhaust nozzle with cooling channels,compared with that without cooling channels.The highest efficiency of the heat transfer is achieved for the cooling channel with rectangular cross section,compared with that with circular and fan-shaped cross sections,and the average temperature at the end face drops by 4.64%.The efficiency of the heat transfer is further improved for the spiral cooling channel,compared with that with the straight cooling channel.The average temperature at the end face of the spiral cooling channel with rectangular cross section drops by 5.17%.The research results are meaningful for the design of exhaust nozzles of aerospace engines. |
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