中文摘要：

为考察喷管壁面气膜冷却以及红外辐射特性对高性能航空发动机壁温分布的影响，对燃气红外波带的光谱特性采用窄波段模型计算，对壁面-燃气辐射采用封闭腔模型计算，对喷管收敛段的气膜冷却采用绝热温比计算。对于包含喷管壁面、隔热屏、套筒的多层结构传热建立壁温一热流耦合的热平衡方程，用Newton—Raphson求解得到喷管及内外结构的壁温。对NASATND-1988中试验台架发动机喷管扩张段的气膜冷却及壁温进行验证计算，并详细计算了收敛段采用多排缝槽气膜冷却的轴对称矢量喷管。结果表明：气膜冷却有效降低了喷管收敛段的壁温，使得喷管扩张段成为受热严峻的部位；扩张段偏转改变了扩张段壁面温度和红外辐射的圆周分布，沿偏转方向的壁温和红外辐射都明显低于偏转反方向的，2个方向上的平均壁温相差约4．8％，喷管在后半球的辐射沿偏转方向增强。数值模拟结果与试验测量值吻合良好，可用于发动机喷管壁温分布精确计算。

英文摘要：

To study the influence of film-cooling and infrared characteristics on a high performance aeroengine, the gas spectral characteristics in infrared band was computed with the narrow band model. The wall gas-radiation was considered with enclosure model and the calculation of film cooling was performed using adiabatic fiml cooling effectiveness method. A coupled heat balance equation of heat flux and wall temperature was established on the multi-layer structure of nozzle including the wall, heat shield and the outer shied. The temperature distribution of nozzle wall was obtained by Newton-Raphson method. An experimental nozzle in NASA TN D-1988 was investigated for verification,and vectoring nozzle with muhi-row of film cooling was also investigated. The results show that film cooling descend the wall temperature of convergent part remarkably, making the divergent part the most heated part. The deflection of the nozzle changed the circumferential distribution of the wall temperature and infrared radiation, both of which are less than the opposite direction of deflection. Radiation to the rear semisphere is amplified in the deflection direction. The simulation results agree well with the experiment measurement results, the method can be used in the precise calculation of nozzle wall temperature calculation.