超燃冲压发动机燃烧室主被动复合热防护干涉机制研究

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中图分类号：V233 文献标志码：A文章编号：1006-0316（2026）01-0008-08

Abstract ： This paper focuses on the thermal protection issues faced by scramjet combustors，constructing a three-dimensional multi-physicscoupling model for active-passive composite thermal protection.It integrates theflow and heat transfer characteristics of hydrocarbon fuels under supercritical pressure with structural mechanical responses，considering both the active cooling mechanism ofconvective heat transfer of fuels in coolingchannels and the heat insulation and conduction laws of the passive layer，thereby realizing numerical calculations of the complex heat transfer-mechanical behaviors of the composite thermal protection system.The study explores the temperature gradient distribution laws of the active and passive thermal protection layers along the thicknessand axial directions，and reveals the thermal expansion evolution characteristics of the two-layer structure in high-temperature environments as well as the formation and distribution mechanism of interface gaps. Research shows that the thermal insulation performance of the passive thermal protection layer bears more thermal load;however，the inherent differences in thermal conductivityand thermal expansion coeffcient between the active and passive layer materials，combined with the non-uniform temperature fields along the layer thicknessand axial directions，lead to asynchronous thermal deformationof the two-layer structure， ultimately forming local contact gaps at the interface.

Key words ：thermal expansion icontact gap iactive-passive composite thermal protection iregenerative cooling

超燃冲压发动机是高超声速巡航导弹的理想动力装置。（剩余7680字）