基于亥姆霍兹共振器的中心分级燃烧室燃烧振荡控制  

Control of combustion oscillation in a central-staged combustor based on Helmholtz resonator

作　　者：严熙成 韩猛 韩啸[1] 张弛[1] 王建臣[1] 何沛 高贤智 YAN Xicheng;HAN Meng;HAN Xiao;ZHANG Chi;WANG Jianchen;HE Pei;GAO Xianzhi(Research Institute of Aero-Engine,Beihang University,Beijing 100191,China;AECC Commercial Aircraft Engine Co.,Ltd.,Shanghai 200241,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]中国航发商用航空发动机有限责任公司,上海200241

出　　处：《北京航空航天大学学报》2024年第12期3854-3862,共9页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金(52106128);国家科技重大专项(J2019-Ⅲ-0002-0045);中央高校基本科研业务费专项资金。

摘　　要：中心分级贫油预混预蒸发(LPP)燃烧室被广泛用于航空发动机和燃气轮机中用于降低排放。但是此类燃烧室在运行过程中遇到了较多的燃烧振荡问题。研究了亥姆霍兹共振器对航空发动机中心分级LPP燃烧室中燃烧振荡的控制效果。实验在以液态航空煤油为燃料的单头部模型燃烧室上开展,涉及中温中压和高温高压2种工况环境。基于声学仿真结果设计了紧凑的亥姆霍兹共振器,体积仅为80 mL和160 mL。实验结果表明,工作频率与燃烧振荡频率相近的亥姆霍兹共振器能显著降低振荡的幅值。中温中压实验中,在火焰分级比25.1%、头部当量比0.6的工况下,亥姆霍兹共振器能完全消除燃烧振荡;高温高压实验中,振荡幅值降低约90%。同时,设计合理的共振器在不同分级比下控制效果略有不同,振荡幅值下降幅度为69.9%~98.9%。另外,声学仿真结果显示,共振器的加入对系统的声学特征模态影响极小,与实验结果吻合。结构紧凑的亥姆霍兹共振器具有在航空发动机LPP燃烧室中抑制燃烧振荡的潜力。Lean premixed pre-vaporized(LPP)combustion technology is widely used in centrally staged combustors of aero engines to reduce pollutant emissions.However,such combustors are prone to combustion instability.The control effect of the Helmholtz resonator on combustion oscillation in a central-staged LPP combustor of an aero-engine was studied.The experiment was carried out on a single-head model combustor with liquid aviation kerosene as fuel,involving two working conditions:medium temperature and medium pressure,as well as high temperature and high pressure.According to the acoustic simulation results,compact Helmholtz resonators were designed,with volumes of 80 mL and 160 mL.The experimental results show that Helmholtz resonators with a working frequency close to the combustion oscillation frequency can significantly reduce the oscillation amplitude.In the medium temperature and medium pressure experiment,the Helmholtz resonator can completely eliminate combustion oscillation under the condition of flame stage ratio of 25.1%and head equivalent ratio of 0.6.In the high temperature and high pressure experiment,the oscillation amplitude is reduced by about 90%.In addition,the reasonably designed resonator has slightly different control effects at different stage ratios,with a decrease in oscillation amplitude in the range of 69.9%~98.9%.Meanwhile,the acoustic simulation results show that the addition of a resonator has little effect on the acoustic characteristic modes of the system,which is consistent with the experimental results.In summary,the Helmholtz resonator with a compact structure has the potential to suppress combustion oscillations in an LPP combustor of aero-engine.

关 键 词：亥姆霍兹共振器 被动控制 燃烧振荡 贫油预混燃烧室 航空发动机 

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]