燃烧室内亚/超临界航空煤油燃烧性能对比实验研究

In order to investigate the combustion performance of sub/supercritical kerosene in an aircraft engine model combustion chamber，based on a single-cup model combustion chamber，an experimental platform for evaluating the combustion performance of sub/supercritical kerosene is constructed. Stable combustion of sub/ supercritical aviation kerosene was achieved in the model combustion chamber. Experiments were conducted to study the combustion performance under different fuel-to-air ratios，kerosene phases，air flow rates and air inlet temperatures. The impact of the operating condition parameters of the combustion chamber on the performance parameters of combustion was determined. The dimensionless temperature（T_x/T_4avg）is defined as the ratio of the thermocouple-measured temperature（T_x）to the average outlet temperature（T_4avg）. The dimensionless height （y/H）represents the radial position（y）normalized by the total radial height（H）. The experimental results that：under subcritical conditions，T_x/T_4avg >1 occurs at y/H=0.35~0.75，while under supercritical states，this range expands to y/H=0.2~0.8. Supercritical kerosene combustion broadens the outlet’s core temperature region. When the combustor inlet air temperature increases from 574 K to 675 K，the overall temperature distribution factor （OTDF）decreases by 20.93%. The utilizing aviation kerosene in a supercritical state within the combustion chamber enhances both the parameters related to its combustion performance and expands significantly the operational range for high-temperature combustors. Except for the total pressure recovery coefficient of the combustor being lower than that in the subcritical phase，both the outlet temperature distribution uniformity and combustion efficiency are higher than those under subcritical combustion conditions.