火箭推进2026，Vol.52Issue(2)：49-60,12.DOI:10.3969/j.issn.1672-9374.2026.02.006
高温壁面条件下冷却液膜传热特性的数值分析
Numerical analysis on heat transfer characteristics of cooling liquid film under high-temperature wall conditions
摘要
Abstract
To explore the film cooling performance of low-thrust liquid rocket engines under high-temperature wall conditions,this study develops a three-dimensional CFD model that couples solid heat conduction,gas-liquid interface deformation,and multiphase phase-change processes.The model captures key behaviors of the liquid film,including impingement,spreading,evaporation,and boiling,using a VOF-level set interface tracking method and Lee phase-change formulation.Numerical results indicate that increasing the initial wall temperature significantly accelerates phase-change intensity,leading to transitions in boiling regimes.This results in a nonlinear reduction of cooling area and in extreme cases,the formation of a continuous vapor layer,which causes local cooling failure.In contrast,increasing jet velocity enhances liquid momentum,promotes film spreading,and strengthens convective heat transfer,thereby alleviating cooling degradation to some extent.A response surface model based on Weber number and dimensionless cooling area(R2=0.986 4)is constructed to quantify the coupled influence of wall temperature and momentum input,successfully identifying cooling effectiveness boundaries.Additionally,the film demonstrates strong spatial heterogeneity,with the impingement region showing the highest heat transfer efficiency,while downstream areas are limited by unstable boiling dynamics.关键词
小推力液体火箭发动机/液膜冷却/高温壁面/冷却面积/冷却响应面Key words
low-thrust liquid rocket engine/liquid film cooling/high-temperature wall/cooling area/cooling response surface分类
航空航天引用本文复制引用
潘见光,饶思航,唐逸豪,韩旺,汪凤山,毛晓芳,姚兆普..高温壁面条件下冷却液膜传热特性的数值分析[J].火箭推进,2026,52(2):49-60,12.基金项目
国家自然科学基金(52376090) （52376090）
国家重点研发计划青年科学家项目(2022YFF0504500) （2022YFF0504500）
CAST创新基金项目,面上创新基金(WYYY-19009.23). （WYYY-19009.23）
