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 1360K

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.