基于SCO_(2)发汗冷却特性的数值研究

Numerical Study on the Transpiration Cooling Characteristics of SCO_(2)

发汗冷却作为一种先进的冷却技术可用于航天器的热防护过程中。进一步提高发汗冷却性能是实现更高效热管理和延长航天器寿命的关键所在。本研究选用物性优于传统冷却工质的超临界二氧化碳(SCO_(2))作为发汗冷却的冷却剂,开展了不同孔隙结构设计下SCO_(2)发汗冷却性能的数值研究,结果表明孔隙率的改变对SCO_(2)冷却剂的流量分配影响明显,发汗冷却板前缘采用较大孔隙率的设计可有效提升冷却性能。基于影响规律,对发汗冷却板进行孔隙结构优化,优化后结构的冷却性能显著提升,平均冷却效率提升至72.46%。

As an advanced thermal protection technique,transpiration cooling can be applied in spacecraft thermal protection systems.Enhancing transpiration cooling performance is essential to achieve more efficient thermal management and extend the lifespan of spacecraft.This study uses supercritical carbon dioxide(SCO_(2)),a superior coolant compared to traditional fluids,for a numerical investigation of transpiration cooling under different pore structure designs.The results indicate that changes in porosity significantly affect the flow distribution of the SCO_(2)coolant.A design with larger porosity at the leading edge of the transpiration cooling panel effectively improves cooling performance.Based on these findings,an optimization of the pore structure was conducted,resulting in a significant enhancement of the cooling performance,with average cooling efficiency increasing to 72.46%.