Capability prediction of high temperature rise center-staged combustor

Based on the increasing demand for high temperature rise combustor of high thrust-mass-ratio aeroengine, a design method of center-staged combustor was given and three-dimensional numerical simulation was conducted on the design model using the same diffuser, outer case and exit dimensions of single annular combustor. The capability of center-staged combustor was compared and analyzed with the numerical simulation results and experimental results obtained from single annular combustor. The results show that, by using the center-staged combustor, the total pressure recovery coefficient can be improved compared with the single annular combustor, and the outlet temperature distribution factor (OTDF) of the combustor is lower than that of single annular combustor in addition to higher temperature rise, but the CO and NO emissions are higher than that of single annular combustor in slow train state. At the designed 0.045 fuel/air ratio state, the temperature rise can reach 1 360 K, and the total pressure recovery coefficient is no less than 0.96; OTDF can be no more than 0.14; the radial temperature distribution factor (RTDF) at outlet can be no more than 0.10, with the combustion efficiency no less than 0.987.