喷注器多孔面板内甲烷发汗冷却特性

Transpiration cooling characteristics of methane in injector porous plate

中文关键词: 发汗冷却  多孔面板  燃烧  甲烷  孔隙率

英文关键词: transpiration cooling  porous plate  combustion  methane  porosity

中文摘要:

      推力室内部极端热环境易引发关键部件的烧蚀损伤，发汗冷却技术是解决飞行器热防护问题的重要途径。针对推力室中喷注器多孔面板甲烷发汗冷却的传热特性复杂及实际燃烧环境耦合等问题，基于涡耗散模型描述甲烷-氧气燃烧过程，考虑多孔结构中固体骨架和流体间的局部热平衡，研究了燃烧过程中喷注器多孔面板内甲烷的发汗冷却特性，探索了冷却剂入口压力和多孔结构参数对发汗冷却性能的影响规律。结果表明：冷却剂入口压力从 6.2MPa 提升至 10.2MPa 时，冷却效率提升至 91.12%；增大孔隙率能提升冷却效率，孔隙率从 0.13 提升至 0.33 时，多孔板最高温度下降38.25%；导热系数增加导致多孔板承受的热流密度增加，冷却性能下降。研究结果为飞行器关键部位的热防护提供了理论支撑。

英文摘要:

      The extreme thermal environment inside the thrust chamber is prone to causing ablation damage to key components, and the transpiration cooling is an important approach to solve the thermal protection prob-lem of aircraft. Aiming at the problems such as the complex heat transfer characteristics of methane tran-spiration cooling in porous injector plate and the coupling of the actual combustion environment in thrust chamber, the study describes the methane-oxygen combustion process based on the eddy dissipation model, considers the local thermal equilibrium characteristics between the solid skeleton and fluid in the porous structure, investigated the methane transpiration cooling characteristics within the porous injector plate during combustion, and explores the influence of coolant inlet pressure and porous structure parameters on transpiration cooling performance. The results show that when coolant inlet pressure increases from 6.2 MPa to 10.2 MPa, the cooling efficiency rises to 91.12%. Increasing the porosity enhances the cooling efficiency: when the porosity increases from 0.13 to 0.33, the maximum temperature of the porous plate decreases by 38.25%. An increase in thermal conductivity leads to higher heat flux on the porous plate, sharp temperature rise, and reduces cooling performance. The research findings provide a theoretical basis for the thermal protection design of key components in thrust chambers.