双级轴向旋流器设计参数对燃烧室点火性能影响规律  

Effects of design parameters of two-stage axial swirler on combustor ignition performance

作　　者：王金铎 惠鑫[1] 武济泓 蒋尧 林宇震[1] WANG Jinduo;HUI Xin;WU Jihong;JIANG Yao;LIN Yuzhen(Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;Xi’an Aircraft Industry Group Company,Limited,Aviation Industry Corporation of China,Limited,Xi’an 710089,China;Hunan Aviation Powerplant Research Institute,Aero Engine Corporation of China,Zhuzhou Hunan 412002,China)

机构地区：[1]北京航空航天大学航空发动机研究院,北京100191 [2]中国航空工业集团有限公司西安飞机工业集团股份有限公司,西安710089 [3]中国航发湖南动力机械研究所,湖南株洲412002

出　　处：《航空动力学报》2022年第11期2544-2552,共9页Journal of Aerospace Power

基　　金：中国航空发动机集团产学研合作项目(HFZL2021CXY003)。

摘　　要：为有效提升航空发动机燃烧室点火性能,以双级轴向旋流器为研究对象,采用三种气动结构参数为设计变量,开展了旋流器优化设计与燃烧室点火性能研究。研究通过试验测量了不同旋流器匹配的单头部燃烧室地面点火与模拟高空点火油气比,获得了旋流器气动结构参数与燃烧室点火性能之间的关联。研究结果表明:在保持总有效面积和内旋流数不变条件下,外旋流数从1.77增加至2.15时,燃烧室点火性能呈现先降低后升高的趋势,较小外旋流数点火特性更佳;内外有效面积比对高空低压工况燃烧室点火性能影响显著,在比值为3∶7时点火特性最佳。在保持其他结构参数不变条件下,文氏管喉道半径对燃烧室高空点火性能影响显著,喉道半径为8 mm时具有较好点火特性。To improve the ignition performance of the aero-engine combustor,different configurations of two-stage axial swirlers were designed based on the swirler design parameters. Ground and high-altitude ignition tests were carried out to obtain the ignition fuel-air-ratios for a model combustor equipped with the designed swirlers. The effects of outer swirl number,the air split ratio between the inner and outer swirlers,and Venturi throat size on combustor ignition performance were analyzed. The results showed that under the same total air flow rate and inner swirl number,when the outer swirl number increased from 1.77 to2.15,the combustor ignition performance first decreased and then increased,and the ignition characteristic was better when the outer swirl number was smaller. The inner and outer swirler flow ratios had a significant impact on the combustor ignition performance under high altitude and low pressure conditions,and the ignition characteristic was the best when the ratio was 3∶7. If other structural parameters were kept unchanged, the Venturi throat radius had a significant impact on the high altitude ignition performance of the combustor,and it had good ignition characteristics when the throat radius was 8 mm.

关 键 词：燃烧室点火性能 双级轴向旋流器 旋流强度 有效面积 文氏管喉道 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]