摘要
为了满足新一代加力燃烧室进口温度的上升需求,有必要对内锥进行气膜冷却以降低其红外辐射。本文主要以试验和数值模拟相结合的方法,研究内锥的气膜冷却特性,找出中心锥的热点。结果表明:未冷却条件下,支板前缘和尾缘附近,内锥壁温较高;在5%冷气条件下,由于内锥前段冷却气膜覆盖不均匀,冷却效果较差,而内锥尖部由于回流区的影响,部分冷却气膜被吹离壁面,冷却效果一般。而且冷气和燃气密度比越大,冷气更容易贴壁面形成冷却气膜,冷却效率越高。
In order to meet the increasing demand of the inlet temperature of the new generation afterburner, it is necessary to reduce the infrared radiation of the inner cone by film cooling. In this paper, both the experimental method and numerical simulation method are used to study the film cooling characteristics of the inner cone, find the hot spot of the inner cone and optimize the cooling scheme. The results show that the temperature of inner cone wall is higher near the front edge and the trailing edge of strut under uncooled condition;under the condition of 5% cold air, because of the inner cone in uneven cooling film covering, the cooling effect is poorer, and in the inner cone tip, since part of the cooling film is blown away from the wall due to the influence of backflow area, the cooling effect is general. And the greater of density ratio is, the easier it is to form a cooling film on the wall surface, and the higher the cooling efficiency is.
出处
《国际航空航天科学》
2017年第1期17-26,共10页
Journal of Aerospace Science and Technology
