Abstract The need of improved cooling effectiveness for hot components in jet engines has led to new designs of afterburner liners. In the present paper, experiments were performed to reveal the cooling characteristics and flow loss of various sinusoidal corrugated liners for an advanced afterburner. It is found that there are alternate high temperature and low temperature zones corresponding to the wave crests and troughs of the corrugated liner, respectively. Compared to the flat liner, the corrugated liner increases cooling effectiveness by 10 % at the blowing ratio of 0.5, by 4.5 % at the blowing ratio of 3.2. However, the difference in discharge coefficients for these two kinds of liners is only 4.3 %. The increased opening ratio of film holes from 1.42 % to 3.72 % for corrugated liners is able to improve the cooling effectiveness by 9.8 %. However, the discharge coefficient is decreased by 34.1 %. The augment of amplitude of liners can enhance the ram effect of cooling air, which has an advantage to increase the local blowing ratio, and to form good cooling film at the windward of wave troughs. The flow loss is bigger while the cooling effectiveness is enhanced due to the change of amplitude of the liner.

中文翻译：

---

加力燃烧室正弦波纹衬板的油膜冷却试验研究

摘要 提高喷气发动机热部件冷却效率的需求导致了加力燃烧室衬套的新设计。在本文中，进行了实验以揭示用于先进加力燃烧室的各种正弦波纹衬套的冷却特性和流动损失。发现与波纹衬板的波峰和波谷相对应的高温区和低温区交替出现。与扁平衬里相比，波纹衬里在吹塑比为 0.5 时冷却效率提高了 10%，在吹塑比为 3.2 时提高了 4.5%。然而，这两种衬垫的排放系数差异仅为 4.3%。波纹衬垫的薄膜孔开口率从 1.42% 增加到 3.72%，能够将冷却效率提高 9.8%。然而，流量系数降低了 34.1%。衬板振幅的增加可以增强冷却空气的撞击效应，有利于提高局部吹气比，并在波谷的迎风处形成良好的冷却膜。由于衬管振幅的变化，流动损失较大，冷却效果增强。