Based on the Navier Stokes(N-S) equations

the numerical simulation of coupling gas and heat on the integrated computational domain of combustion and nozzle in TBCC(turbine based combined cycle)

including the heat shield

internal and external flow of the heat shield and the outer flow field

was carried out

inconsideration of the gas composition and the radiation heat transfer. The wall temperature distribution of the cylinder and heat shield in the integrated computational domain of combustion and nozzle in TBCC under certain flight condition was mainly studied in addition to the radiation heat flux distribution of heat shield. Results showed that the wall temperature along the intersection of the symmetry and cylinder changed slightly within the range of axial distance from 0.5m to 2.6m. The wall temperature rapidly increased within the range of axial distance from 2.6m to 3.1m

and dramatically decreased within the range of axial distance from 3.1m to 3.5m.Then the wall temperature along the upper intersection decreased gradually

while the wall temperature along the lower intersection increased first and then decreased. The highest wall temperature point(1577K) of the cylinder was contraction section of lower adjusting plate of nozzle. The radiation heat flux of inner wall of the heat shield changed from 370kW/m2 to 500kW/m2

the radiation heat flux decreased first and then increased along the flow

the radiation heat flux of the two intersections was more than 300kW/m2 compare with outer wall

the radiation heat flux of outer wall of the heat shield changed from 50kW/m2 to 200kW/m2.