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| Study on heat transfer efficiency with fluid-solid coupling for Laval nozzle |
| Received:September 16, 2023 Revised:November 29, 2023 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7511/jslx20230916007 |
| KeyWord:Laval nozzle cooling design spiral channel |
| Author | Institution |
| 杨凯 |
南京理工大学, 机械工程学院, 南京 |
| 唐丹娜 |
南京理工大学 智能制造学院, 南京 |
| 毕聪 |
中国航空发动机研究院, 北京 |
| 王则皓 |
中国航空发动机研究院, 北京 |
| 汤海斌 |
南京理工大学 智能制造学院, 南京 |
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| Abstract: |
| 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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