多种气膜冷却形式下轴对称矢量喷管壁温计算研究

航空发动机矢量喷管的冷却结构设计是研究矢量推进技术应用的关键问题之一。针对某偏转20°轴对称矢量喷管隔热屏采用的十种气膜冷却结构,建立基于壁面传热的热平衡方程,采用牛顿-拉斐尔森迭代法得出十种冷却结构下壁面及隔热屏的温度。其中气膜冷却采用有效温比经验公式计算,燃气辐射采用封闭腔净辐射分析法计算,并把本文计算的壁温与文献结果进行对比分析。结果表明:隔热屏对喷管收敛段有很好的冷却作用,采用气膜冷却可显著降低其温度;相对于受隔热屏保护的收敛段而言,喷管扩张段的受热形势较为严峻,温度更高,其冷却有待加强。

Numerical study on film cooling and wall temperature of vectored axial-symmetric nozzle

The study on the cooling structure of vectoring nozzle is very essential for developing the vectoring propulsion technology in aero-engine .To study the cooling technology of the heat shield on the axial-symmetric vectoring nozzle with 20＆#176; deflection ,the heat balance equation based on heat transfer of nozzle has been devel-oped and solved with Newton-Rafael method to give wall temperature .Heat transfer of film cooling is computed with empirical formula of cooling effectiveness .And radiative heating from the gas is computed with net radia-tion analysis method in an enclosure .To verify the computation method ,wall temperature of a certain axial-symmetric nozzle in after burning condition is computed and compared with the results of reference .Study shows that the heat shield plays a good cooling part for convergent part of nozzle with film cooling reducing its temperature remarkably .Compared with convergent part of nozzle which is protected by the heat shield ,tem-perature of the divergent section of nozzle is much higher and needs further cooling .