For an aeroengine annular combustor model

coherent anti-Stokes Raman scattering (CARS) and tunable diode laser absorption spectroscopy (TDLAS) were used to measure temperature in primary zone (PZ) for modeling condition(Case 2).Based on Fluent 12.0 software

two different non-premixed combustion models equilibrium model (EM) and steady laminar flamelet (SLF) model were adopted to calculate the combustor performances for the same case.Then comparison between spectral measured temperature and numerical simulated one shows that higher and more accurate prediction were achieved by EM.What's more

the errors between EM calculation and CARS measurement are less than 6%.For cold flow condition(Case 1)

not only detailed analysis of flow field in PZ was made

but also the influence of primary jet on recirculation zone was investigated.Because of the advantage EM was used for full pressure condition (Case 3) to analyze reaction flow field in PZ and calculate combustor performances

including combustion efficiency(0.97)

overall temperature distribution factor (OTDF)(0.312)

etc.These results indicate reasonable heat transfer and combustion phenomena in combustor model.