超临界燃油喷射特性受喷嘴长径比影响的实验研究  

Experimental Study on Characteristics of Supercritical Fuel Injection Affected by Nozzle Length-Diameter Ratio

作　　者：申帅[1] 范玮[1] 靳乐[1] 周舟[1] 张晋[1] 李建玲[1] SHEN Shuai;FAN Wei;JIN Le;ZHOU Zhou;ZHANGJin;LIJian-ling(School of Power and Energy,Northwestern Polytechnical University,Xi＇an 710129,China)

机构地区：[1]西北工业大学动力与能源学院,陕西西安710129

出　　处：《推进技术》2018年第10期2363-2369,共7页Journal of Propulsion Technology

基　　金：国家自然科学基金(91441201;51376151);科学挑战计划(TZ201601)

摘　　要：为研究喷嘴构型对超临界燃油喷射特性的影响,采用阴影显微成像系统对超临界RP-3航空煤油喷射到大气环境中的射流特征进行了实验研究,重点分析了喷嘴长径比对喷射扩张角、冷凝长度射流近场激波结构的影响。研究结果表明,超临界燃油喷射时,在喷嘴出口处存在截断激波和马赫盘等激波结构,马赫盘下游会出现工质的冷凝现象,并发现随着喷嘴长径比的增大,射流的喷射扩张角增大且其最大增幅达12.7%,而冷凝长度、马赫盘直径和马赫盘距离均减小,最大降幅分别为15.6%,56.1%和30.4%。In order to obtain the effects of nozzle geometry on supercritical fuel injection characteristics,the performances of the supercritical injection of RP-3 aviation kerosene into a quiescent atmospheric environment were experimentally studied by a microscopic shadowgraphy system. The near-field shock structure,condensation length and jet spreading angle affected by nozzle length-diameter ratio were analyzed in detail. The intercepting shock,Mach disk,and condensation phenomenon downstream of the Mach disk were observed during the injection. With the increasing of the nozzle length-diameter ratio,the condensation length,Mach disk diameter and Mach disk distance were all decreased,and maximum reduction was 15.6%,56.1% and 30.4% respectively,while the jet spreading angle increased,and its maximum increases up to 12.7%.

关 键 词：超临界喷射 长径比 阴影法 RP-3航空煤油 

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]