摘要
运用数值模拟方法,在主流总温920K、冷却空气总温470K的参数条件下,对比分析了塞锥尾缘气膜孔开孔率(1%~4%)、冷却空气用量(4.3%主流质量流量以内)和矢量偏转角(0°~20°)对二元塞式喷管塞锥尾缘冷却和红外辐射的影响。结果表明塞锥尾缘气膜冷却可以有效降低表面温度和喷管红外辐射强度,开孔率为2%的气膜孔阵列的表面降温效果相对较优;冷却空气质量流量比超过2.85%时,塞锥表面温度降低幅度随冷却质量流量比的变化趋于减缓,当冷却空气质量流量比为2.85%时,水平探测面±30°探测角内红外辐射强度相对无冷却喷管下降50%左右,铅垂探测面上气膜冷却表面降温对红外辐射强度的抑制效果更为显著;矢量角对于壁面温度分布影响很小,但对红外辐射强度空间分布具有重要的影响。
A numerical investigation is performed to study cooling and infrared radiation suppression of the plug trailing-body of a two-dimensional plug nozzle at a primary flow total temperature of 920 Kand a cooling flow temperature of 470 K.The effects of the multi-hole perforated percentage（ranging from 1%to 4%）,cooling air usage（limited in 4.3% of the primary mass flow rate）and vector angle（ranging from 0°to 20°）on cooling and infrared radiation suppression of the plug trailingbody are analyzed.The results show that the plug trailing-body cooling has an effective role in decreasing the surface temperature and suppressing infrared radiation intensity.The multi-hole perforated percentage of 2% seems more reasonable.Once coolant usage is increased beyond 2.85% of the primary mass flow rate,the increase of coolant usage has a weak influence on further reduction of surface temperature.The cooling action on the plug trailing-body with coolant usage of 2.85%of the primary mass flow rate is capable of suppressing the infrared radiation intensity about 50% relative to the un-cooled nozzle on the horizontal detective plane.On the vertical detective plane,the cooling action on the plug trailing-body shows more significant influence on infrared radiation suppression.The vector angle has a weak influence on surface temperature distribution.However,the distribution of infrared radiation is seriously affected by vector deflection.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2017年第12期93-100,共8页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(U1508212
51306088)~~
关键词
二元塞式喷管
塞锥冷却
红外辐射抑制
矢量偏转
数值模拟
two-dimensional plug nozzle
plug cooling
infrared radiation suppression
vector deflection
numerical simulation
