凹腔燃烧室对旋转爆震波传播模态和燃烧室推力性能的影响  

Effect of the cavity combustor on the propagation modes of rotating detonations and propulsion performance

作　　者：王致程 严宇 王可[2] 范玮[2] 杨宝娥 胡洪波 赵明皓 WANG Zhicheng;YAN Yu;WANG Ke;FAN Wei;YANG Bao’e;HU Hongbo;ZHAO Minghao(National Key Laboratory of Science and Technology on Liquid Rocket Engines,Xi’an Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Xi’an 710100,China;School of Power and Energy,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]中国航天科技集团有限公司、西安航天动力研究所、液体火箭发动机技术重点实验室,西安710100 [2]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2023年第6期1306-1315,共10页Journal of Aerospace Power

基　　金：陕西省自然科学基础研究计划(2022JQ-490);重点实验室基金(HTKJ2022KL011002);国家自然科学基金委员会面上项目(52076181)。

摘　　要：为研究凹腔燃烧室对旋转爆震波模态和燃烧室推进性能的影响,分别基于凹腔燃烧室、宽度19 mm和宽度15 mm的环形燃烧室,以乙烯和富氧空气为推进剂,氧化剂流量范围为50~200 g/s,当量比为0.8,在未安装和安装塞式喷管条件下开展了对比实验。未安装塞式喷管条件下,凹腔燃烧室和环形燃烧室中均得到了双波对撞模态和单波模态,且分布规律基本相同,但凹腔燃烧室中旋转爆震波的传播速度明显高于环形燃烧室,推进剂供给流量越低趋势越明显,说明凹腔结构可以改善推进剂的混合效果,减小爆震波的速度亏损。安装塞式喷管后,爆震波的传播模态发生了变化,不同燃烧室构型中得到了缓燃模态、双波对撞模态、四波对撞模态、单波模态和双波模态。凹腔燃烧室中爆震波以单波或双波模态稳定传播的工况范围较宽,爆震波速度亏损更小,环形燃烧室中爆震波稳定传播的工况范围较窄,主要以双波对撞或者四波对撞模态传播。最后,对比不同燃烧室条件下的混合物比冲发现,凹腔燃烧室的混合物比冲低于环形燃烧室,与宽度为15 mm的环形燃烧室相比比冲下降了约10%,与宽度为19 mm的环形燃烧室相比比冲平均下降了约7%。上述研究表明凹腔燃烧室有利于旋转爆震波的稳定传播,减小爆震波的速度亏损,但凹腔结构会降低燃烧室的推进性能。To investigate the effect of the cavity combustor on the propagation modes of rotating detonation waves and propulsion performance,experimental study was performed in a laboratory-scale rotating detonation combustor utilizing different combustor configurations including a cavity combustor,two annular combustors with the combustor width of 19 mm and 15 mm,respectively.Ethylene and oxygen-enriched air was used as propellants.The mass flow rate of oxidizer varied from 50 g/s to 200 g/s and the equivalence ratio was fixed at 0.8.The experiments have been conducted in the combustor with and without installing the aerospike nozzles,respectively.For the combustor without installing the nozzle,the dual-wave collision mode and the single detonation mode were obtained and the mass flow rate ranges of different modes were identical for different combustors.For the cavity combustor,the propagation velocity was faster than the values measured from the annular combustors,especially at lower mass flow rate.This phenomenon indicated that more homogeneous mixtures were produced and lower velocity deficit were obtained in the cavity combustor.As the combustors installing with the aerospike nozzles,different propagation modes were observed,including deflagration mode,dual-wave collision,quad-wave collision,single detonation mode and dual wave mode.The stable co-rotating detonations were easily obtained with a wide range of mass flow rate in the cavity combustor,while the detonation counterrotating detonations were easily acquired at the same operation conditions.Finally,it was found that specific impulse calculated from the cavity combustor decreased by 10% compared with the annular combustor of width 15 mm,and by 7% compared with the annular one of width 19 mm,respectively.In summary,the cavity combustor was beneficial for promoting the stability and reducing the velocity deficit of rotating detonations,but this configuration was adverse for the propulsion performance.

关 键 词：旋转爆震波 凹腔燃烧室 环形燃烧室 传播模态 传播速度 比冲 

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]