Design and performance analysis of supercritical carbon dioxide supersonic nozzle

被引：0
|
作者：
Zhao R. [1 ]
Li Y. [1 ]
Zhao Y. [1 ]
Wu J. [1 ]
机构：
[1] College of Aerospace Science and Engineering, National University of Defense Technology, Changsha
来源：
Zhao, Yuxin (zyx_nudt@163.com) | 1600年 / Journal of Propulsion Technology卷 / 45期
基金：
中国国家自然科学基金;
关键词：
Method of characteristics; Performance analysis; Real gas effect; Supercritical carbon dioxide; Supersonic nozzle;
D O I：
10.13675/j.cnki.tjjs.2210069
中图分类号：
学科分类号：
摘要：
Supercritical carbon dioxide is widely used due to its unique physical properties. The real gas effect of supercritical carbon dioxide is significant,and its flow mechanism is quite different from that of ideal gas, so it is necessary to design corresponding nozzles. The supercritical carbon dioxide supersonic nozzle was designed using method of characteristics,in which the thermodynamic parameters of carbon dioxide were obtained based on the S-W equation. The nozzle contour was corrected for boundary layer effect based on CFD viscous simulation. The effects of changing the total pressure and total temperature at the nozzle inlet on the flow field in the nozzle were analyzed. The results show that under design condition,the difference between mass-average Mach number and the design value at the nozzle outlet is 0.033% and the flow field quality in the nozzle is good. Under off-design conditions,because the change in temperature will significantly change the thermophysical parameters of CO2,the effect of inlet total temperature on nozzle flow field is greater than that of inlet total pressure. When the inlet total pressure and temperature are reduced by 83.33% and 52.94% respectively,the Mach number at nozzle outlet decreases by 1.16% and increases by 3.23% respectively.The flow field in the nozzle meets the design requirements under the design condition,and the deviation between Mach number at nozzle outlet and design value is small under off-design conditions. Therefore,the nozzle can work under a wide range of conditions. © 2024 Journal of Propulsion Technology. All rights reserved.
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