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航改型双环燃烧室燃烧反应特性试验

刘爱虢 朱悦 陈保东 刘凯 曾文 王成军

刘爱虢, 朱悦, 陈保东, 刘凯, 曾文, 王成军. 航改型双环燃烧室燃烧反应特性试验[J]. 航空动力学报, 2017, 32(8): 1793-1800. doi: 10.13224/j.cnki.jasp.2017.08.001
引用本文: 刘爱虢, 朱悦, 陈保东, 刘凯, 曾文, 王成军. 航改型双环燃烧室燃烧反应特性试验[J]. 航空动力学报, 2017, 32(8): 1793-1800. doi: 10.13224/j.cnki.jasp.2017.08.001
Experiment on combustion characteristics of aeroderivative gas turbine twins annular combustor[J]. Journal of Aerospace Power, 2017, 32(8): 1793-1800. doi: 10.13224/j.cnki.jasp.2017.08.001
Citation: Experiment on combustion characteristics of aeroderivative gas turbine twins annular combustor[J]. Journal of Aerospace Power, 2017, 32(8): 1793-1800. doi: 10.13224/j.cnki.jasp.2017.08.001

航改型双环燃烧室燃烧反应特性试验

doi: 10.13224/j.cnki.jasp.2017.08.001
基金项目: 国家自然科学基金(51476106); 航空基金(2015ZB54003)

Experiment on combustion characteristics of aeroderivative gas turbine twins annular combustor

  • 摘要: 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。

     

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出版历程
  • 收稿日期:  2015-12-09
  • 刊出日期:  2017-08-28

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