旋流器以及火焰筒结构对贫油直喷燃烧室的燃烧性能影响

Effect of Structure of Swirler and Combustion Liner on Combustion Performance of Lean Direct Injection Combustor

基于对优化使用贫油直喷(LDI)燃烧室的航空发动机提高燃烧效率、降低有害排放的需求,本文通过燃烧试验研究探讨了火焰筒出口尺寸可改变的单元贫油直喷燃烧室,在使用不同结构的旋流器时的燃烧性能(旋流叶片安装角为55?)。试验中分别测试了使用单级轴向旋流器,同向双级轴向旋流器以及反向双级轴向旋流器的单元LDI燃烧室的燃烧性能。并且在每次燃烧试验中,测试了火焰筒出口面积从100%逐步缩小至25%对燃烧效果的影响。基于对燃烧效果的分析,探讨了旋流器结构以及火焰筒结构对燃料与空气混合速率以及效果、生成火焰形状和稳定性以及燃烧效率的影响。

Based on the need of optimization of aero-engines that use lean direct injection(LDI)combustors to increase their combustion efficiency and reduce harmful emissions,in this paper,the combustion performance of a single element LDI combustion chamber with variable combustion liner exit area and a swirler with 55?vane angles is studied through three combustion test cases.The combustion effect of the LDI combustion chamber using a single axial swirler,a co-rotating two-stage axial swirler and a counter-rotating two-stage axial swirler is tested separately in each test case.Furthermore,in each test case,the effect of the combustion liner exit area decreasing from 100%to 25%on the combustion effect was tested.Based on the analysis of combustion effect,the influence of swirler structure and combustion liner structure on fuel and air mixing rate and efficiency,flame shape and stability and combustion efficiency is discussed.