Abstract: With a view to study heat transfer process occurring in vectored nozzle installed in aero engine,convection and radiation heat transfer and 2 D distribution of wall temperature in nozzle are computed in this paper.Related cooling method for heated parts are considered and cooling effectivenesses of different film types on expandable regulating part of nozzle are compared.Computation of radiation heat transfer is carry out for a series of spectrums and 3 D distribution of gas temperature and pressure is considered.A general program suitable for axisymmetric symmetrical vectored nozzle,circular to rectangular vectored nozzle and spherical traversing vectored nozzle,both in after burning condition and non after burning condition is developed and computed results of several samples are presented.The results show that the temperature of deflected vectored nozzle varies apparently along the circumference,temperature along the deflecting direction is lower than that of the opposite direction.