三级旋流器旋流角匹配影响双环预混旋流燃烧室燃烧性能试验

Experiment on Effects of Triple Swirler Swirl Angle Matching on Combustion Performance of Twins Annular Premixing Swirler Combustor

为研究地面用燃气轮机以0号柴油为燃料时的燃烧特性,对装有值班级直射式喷嘴和5种旋流器组合方案的双环预混旋流(Twins Annular Premixing Swirler,TAPS)燃烧室的特性进行了实验测试,获得了5种旋流器组合方式下燃烧室的流阻性能和燃烧性能。研究结果表明:双环预混旋流燃烧室的总压恢复系数都在0.97以上,高于经典的单环腔燃烧室;值班级采用直射式喷嘴会导致燃烧室的点火和CO排放性能下降,点火油气比在0.04以上,CO排放高于36g/kg;随值班级旋流角增大,可改善点火性能,最低点火油气比可达到0.04左右,加宽贫油熄火边界,慢车贫油熄火边界可低至0.0058;燃烧室入口温度升高可以使燃烧室点火油气比下降30%,贫油熄火油气比下降35%;5种旋流器组合方式下,NO_x和UHC的排放最低达到了1.1g/kg和3.85g/kg,满足低排放燃烧室的要求,冒烟指数达到了无烟燃烧室的标准,CO排放最高达到了51.84g/kg远高于要求值,燃烧效率最高为0.987,低于先进燃气轮机对燃烧效率的要求。

Experiments were conducted to study the combustion performance of gas turbine combustor with No.0 diesel as fuel. The combustor is twins annular premixing swirler（TAPS） combustor with direct injection nozzle for the pilot stage and 5 kinds of swirler combination schemes. The flow resistance and combustion performances for different combination of swirlers have been achieved. The test results show that the total pressure recovery coefficient of the TAPS combustor is over 0.97,which is higher than that of the classical single annular combustor. The direct injection nozzle of pilot stage can lead to ignition and CO emission performance degradation,the ignition fuel-air ratio is higher than 0.04 and CO emission is higher than 36g/kg. The ignition performance and lean blowout limits can be improved with the increases of pilot stage swirler angle,the minimum ignition fuel-air ratio can reach 0.04 and the idle lean blowout can be as low as 0.0058. The increasement of combutor inlet can decrease 30% and 35% of the fuel-air ratio for ignition and idle lean blowout. The lowest UHC and NO_x emissions can reach 1.1g/kg and 3.85g/kg respectively for the 5 kinds of swirler combination schemes to meet the requirements of low emission combustor. The smoke number reaches a smokeless combustor standard at all the studied cases,but CO emission level is higher than the requirements to 51.84g/kg. The maximum combustion efficiency is 0.987,which is lower than that of the advanced gas turbine.