摘要
针对液体火箭发动机层板发汗冷却推力室的结构层板可能出现受热皱损的问题,采用三边简支、一边自由的矩形薄板假设,对结构层板的扩散流动区进行稳定性问题的讨论。分析了典型结构的层板发汗冷却推力室由热应力引起的变形,获得了结构层板发汗缝隙宽度和层板厚度之间的关系,并通过算例说明了避免层板受热皱损的设计计算方法。
Heat transfer possibly results in the thermal wrinkling of transpiration cooling plateler for the liquid rocket engine＇s thrust chamber. A rectangular sheet which has 3 freely-supported sides and 1 free side is assumed. Stability in the diffusion flow field of the formed platelet is discussed. Deformation caused by thermal stress in the typical structure of the platelet thrust chamber is analyzed. The relationship formula between the width of the transpiration gap and the thickness of the platelet is obtained, Design and calculation rnethod to avoid thermal wrinkling of the platelet is given by a case study.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2006年第2期241-244,共4页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(50276067)资助项目
关键词
发汗冷却
层板结构
热皱损
火箭发动机
热应力
transpiration cooling
formed platelet
thermal wrinkling
rocket engine
thermal stress
