旋流器构型对全环燃烧室性能的影响  

Effects of swirler configuration on characteristic of full annular combustor

作　　者：龚卡 王志凯 刘逸博 陈盛 罗莲军 蒋尧 GONG Ka;WANG Zhikai;LIU Yibo;CHEN Sheng;LUO Lianjun;JIANG Yao(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]西北工业大学动力与能源学院,陕西西安710129

出　　处：《推进技术》2024年第11期89-96,共8页Journal of Propulsion Technology

摘　　要：为研究旋流器构型对燃烧室性能的影响,针对配装双级轴向旋流器和双级径向旋流器的全环燃烧室开展了实验研究。结果表明,在本文研究范围内,地面点火状态下,轴向方案和径向方案点火油气比分别为0.011~0.022和0.015~0.026,轴向方案比径向方案具有更宽的点火边界。轴向方案贫油熄火油气比为0.009~0.020,径向方案贫油熄火油气比为0.006~0.019,径向方案比轴向方案具有更宽的贫油熄火边界。在地面慢车和空中慢车状态下,轴向方案比径向方案具有更好的出口温度分布品质。轴向旋流器对应的燃烧室压力脉动强度显著强于径向涡流器:油气比为0.011时,轴向方案和径向方案的燃烧室主频分别为525 Hz和555 Hz,相对压力脉动分别为1.9%和0.3%;油气比为0.018时,轴向方案的燃烧室主频为475 Hz,相对压力脉动为1.1%,而径向方案无明显主频。To study the effects of swirler configurations on the performance of combustor,experimental re⁃search was conducted on a full annular combustor equipped with dual-axial swirlers and dual-radial swirlers.Within the scope of this study,the results indicate that the ignition fuel-air ratio ranges from 0.011 to 0.022 for the axial scheme and from 0.015 to 0.026 for the radial scheme under ground ignition condition.The axial scheme has a wider ignition limit compared to the radial scheme.The lean blowout fuel-air ratio ranges from 0.009 to 0.020 for the axial scheme and from 0.006 to 0.019 for the radial scheme.The radial scheme has a wider lean blowout limit compared to the axial scheme.Under ground idle and flight idle conditions,the axial scheme exhib⁃its better quality of outlet temperature distribution compared to the radial scheme.The pressure fluctuation inten⁃sity in the combustor corresponding to the axial swirler is significantly stronger than that of the radial swirler.At a fuel-air ratio of 0.011,the axial scheme and radial scheme have combustor dominant frequencies of 525 Hz and 555 Hz,and relative pressure fluctuations of 1.9%and 0.3%,respectively.At a fuel-air ratio of 0.018,the axial scheme has a combustor dominant frequency of 475 Hz and a relative pressure fluctuation of 1.1%,while the radi⁃al scheme does not exhibit a significant dominant frequency.

关 键 词：全环燃烧室 旋流器 点火性能 贫油熄火 压力脉动 实验研究 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]