Optical measurement and characteristic analysis of aeroengine combustor primary zone with counter-rotating swirler

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.