To solve technical difficulties resulting from high temperature rise and low emission of new generation engine combustor

a single tube combustor model with tangential effusion cooling technology was designed.Numerical simulation was conducted to study the flow field characteristics and wall temperature distribution of combustor liner by solving Navier-Stokes (N-S) equations with thermal fluid-solid coupling method.The liner wall temperature distribution was computed under two conditions by three-dimensional coordinate system

the fuel particle trajectory by Lagrange method

the combustion by non-premixed model

the radiation by discrete ordinates model

the turbulence by the standard k-ε model

and the neighborhood of the solid wall by the wall-function.The results show that

at the 0.046 fuel-air ratio condition

30% cooling air mass fraction

830K inlet air total temperature and 3MPa inlet air total pressure

the maximum wall temperature is 1015K and the maximum temperature gradient is 22.5K/cm

which meet the need of wall temperature level for 12 thrust-mass ratio military engines and low emission civil engines at 30% cooling air mass fraction

and 0.046 fuel-air ratio condition.