摘要
建立了包括加力燃烧室隔热屏在内的轴对称矢量喷管内外流一体化流场计算模型,重点研究了某涡扇发动机隔热屏位置对矢量喷管扩张段壁温及通过矢量喷管喷口发射的红外辐射强度的影响.结果表明:基于密度求解器求解包含隔热屏在内的矢量喷管内外流一体化的跨声速流场、温度场和质量分数场是成功的;随着隔热屏覆盖喷管收敛段的长度增加,喷管扩张段壁温呈现出先下降而后上升的规律,存在一个最佳的隔热屏位置.最后利用作者提出的离散净辐射法,编制程序计算得到了隔热屏位置对通过喷管喷口发射的红外辐射强度的影响规律.
The inner and outer flow field,temperature field and gas concentration field models including the heat shield in the after burning room of a vectored nozzle were established and computed.The effect of the heat shield position on the inner wall,i.e.the heat shield and the nozzle wall,temperature distribution and the corresponding infrared characteristics was studied.The results show that the transonic flow field solution governed by the Navier-Stokes equations based on the density solver is successful.The wa...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第7期1437-1442,共6页
Journal of Aerospace Power
关键词
矢量喷管
隔热屏位置
壁温
红外特征
离散净辐射法
vectored nozzle
heat shield position
wall temperature
infrared characteristics
discrete net-radiation method