Numerical study of tangential effusion cooling for combustor liner

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.