侧喷式一体化支板火焰稳定器液雾分布试验  

Experiment on spray distribution of an integrated strut flameholder with cross injection

作　　者：张权 刘玉英[1] 谢奕[1] 高昭 刘广海[1] ZHANG Quan;LIU Yuying;XIE Yi;GAO Zhao;LIU Guanghai(School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《航空动力学报》2023年第3期607-617,共11页Journal of Aerospace Power

基　　金：国家科技重大专项(J2019-Ⅲ-0016-0060)。

摘　　要：在常温常压、来流马赫数为0.182及液气动量比为10~70的条件下,以水为雾化介质,采用激光片光照相法开展了侧喷式一体化支板火焰稳定器的液雾分布特点研究,并探讨了液气动量比及喷射位置对液雾分布轨迹的影响规律。研究表明:侧喷式一体化支板火焰稳定器液雾分布的外轨迹与横向射流类似,内轨迹受稳定器回流区卷吸作用的影响而弯向回流区,且在低液气动量比条件下影响显著。液气动量比是影响一体化支板火焰稳定器喷雾内外轨迹的重要因素,液气动量比增加,液雾穿透深度增加。喷射位置对液雾外轨迹的影响较小,但对内轨迹影响显著;过近或过远的喷射距离均不利于回流区对液雾的卷吸,这与液雾喷射和稳定器的近距耦合有关。The liquid spray distribution characteristics of a kind of integrated strut flameholder(ISF)with cross injection were studied with water,under the conditions of ambient temperature and pressure,incoming flow Mach number 0.182 and liquid-air momentum ratio range from 10 to 70,using laser sheet/photography.The effect of liquid-air momentum ratio and injection position on the distribution trajectory of liquid spray was discussed.The results showed that the outer trajectory of the liquid spray of ISF was similar to that of the crossflow,and the inner trajectory was bent back to the recirculation zone owing to the entrainments of the recirculation zone,which was more significant for low liquid-air momentum ratio condition.The liquid-air momentum ratio served as an important factor for inner and outer trajectory of the spray;the penetration depth of the liquid spray of ISF increased with the increase of liquid-air momentum ratio.The injection position of ISF had little influence on the outer trajectory of the liquid spray,but had a significant influence on the inner trajectory.It was not good for the entrainments of spray into recirculation zone when the injection distance was too far or too close,which was related to the closely coupling of the liquid injection and the flameholder.

关 键 词：一体化支板火焰稳定器 液雾分布轨迹 液气动量比 喷射位置 一体化设计 

分 类 号：V231.23[航空宇航科学与技术—航空宇航推进理论与工程]