三维航空发动机燃烧室非灰气体辐射换热数值模拟

An in-house radiative heat transfer code using discrete ordinates method (DOM) and statistical narrow bands correlated-K (SNBCK) model was demonstrated to be able to calculate the gaseous radiative heat transfer in complex 3D combustion systems accurately and efficiently. After validation by using the benchmark models， the impact of the directional quadrature scheme， spatial differencing scheme， gauss quadrature type and number of quadrature points were studied. The results showed that the accuracy of the directional quadrature scheme with 24 discrete directions was low，and the Thurgood scheme with 32 discrete directions was recommended. Spatial differencing scheme and gauss quadrature type had little effect on results. Finally， the gaseous radiative heat transfer in the combustion chamber of the aero-engine under different pressures and wall temperatures was calculated. It showed that the maximum values of radiative source term in the flame zone and next to the wall were about 6 000 kW/m³ and 17 000 kW/m³， respectively， the maximum wall radiative heat flux can reach to 88 kW/m². Radiative heat transfer increased with higher pressure，and the increasing rate decreased，which was significantly affected by the concentration of the participating medium.