航改型双环燃烧室燃烧反应特性试验

针对地面运输用燃气轮机低排放的要求，试验研究了一种双环预混旋流(TAPS)燃烧室在以0号柴油为燃料时的反应特性。结果表明:采用TAPS燃烧室由于空气分配方式的改变，总压恢复系数在0.97以上，高于经典单环燃烧室。由于柴油黏度和燃点的影响，使用柴油为燃料时最低常压点火油气比高于0.05，要比相同结构采用航空煤油为燃料时的点火油气比高，但慢车贫油熄火极限没有明显的变化，维持在0.006~0.008之间。采用压力雾化的预燃级存在燃料混合不均匀的问题，导致燃烧效率只能达到0.99，为要求值的下限，但燃烧室出口温度分布系数小于0.25，达到了所要求的性能指标。由于采用了预混预蒸发燃烧，污染物排放中NOx的干基体积分数为1.76×10-5，明显低于所要求的性能指标，但CO的干基体积分数较高达到了5.02×10-4。综合比较各项性能指标，该燃烧室在点火、贫油熄火、燃烧室出口温度分布和NOx排放上表现出了一定的优势，但燃烧效率低和CO排放高还是需要解决的问题。 

Experiment on combustion characteristics of aeroderivative gas turbine twins annular combustor

The reaction characteristics of a kind of twins annual premixed swirler(TAPS) combustor were studied using No.0 diesel as fuel in order to satisfy the requirement of low emission of gas turbine for ground transportation. The results showed that, the total pressure recovery coefficient of the TAPS combustor reached more than 0.97, higher than classical single annual combustor due to the changes in air distribution characteristics. The minimum atmospheric ignition fuel-air ratio over 0.05 was higher than that using the aviation kerosene as fuel with the same combustor structure due to the influence of viscosity and flash point, but idle lean blow-out limit had no obvious change between 0.006 and 0.008. The fuel mixing was nonuniform due to pressure atomization at the pilot stage, which caused the lower combustion efficiency 0.99, but the outlet temperature distribution factor was less than 0.25, which can meet the requirement. For the pollution emissions, NOx dry volumn fraction was 1.76×10-5 significantly lower than the required index, but the CO dry volumn fraction was higher up to 5.02×10-4 due to use of the premixed pre-evaporation combustion. Through comprehensive comparison of various performance indicators, the combustor has advantages in ignition, lean blow-out, combustor outlet temperature distribution and NOx emissions, but the lower combustion efficiency and higher CO emission are still problems to be solved.