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近/超临界RP-3航空煤油的喷射特性试验研究

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针对未来先进航空发动机的超临界燃油喷射混合需求,采用纹影系统对近临界和超临界RP-3航空煤油喷射进入静止大气中进行了试验研究,并结合RP-3航空煤油10组分替代物对近/超临界燃油喷射过程进行解析.研究表明:近/超临界燃油喷射会产生激波结构,并且在喷口附近有相变过程,但是近临界和超临界喷射无论是在整体射流结构抑或是近喷嘴处射流结构上都有着不同,与近临界喷射相比,超临界喷射在马赫盘内气相区/液相区更大,再液化距离更长;同时随着喷射温度的增加,马赫盘直径和纵向距离以及射流扩张角均会减小,而随着喷射压力的增加,马赫盘直径和纵向距离以及射流扩张角均会增加.
Experimental study on injection characteristics of near/supercritical RP-3 aviation kerosene
In order to meet the requirements of supercritical fuel injection for Advanced Aero Engines in the future,the schlieren system was used to conduct experimental research on the injection of near/supercritical RP-3 aviation kerosene into the still atmosphere,and the process was analyzed by combining with the 10-component substitute of RP-3 aviation kerosene.The results revealed that near/supercritical fuel injection could produce shock wave structure and phase transition near the nozzle exit.However,there were differences between near critical and supercritical jets in the overall jet structure or the jet structure near the nozzle.Compared with the near critical injection,the supercritical injection was larger in the gas-phase region/liquid-phase region in the Mach disk,and had a longer reliquefication distance;at the same time,with the increase of injection temperature,Mach-disk diameter,longitudinal distance and jet expansion angle all decreased.But with the increase of injection pressure,Mach-disk diameter,longitudinal distance and jet expansion angle increased.

near/supercritical injectionRP-3 aviation kerosene10-component substitutejet structurephase transition

葛浩、范育新、王伟利、岳晨、曹程皓、刘易安

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南京航空航天大学能源与动力学院,南京 210016

北京动力机械研究所,北京 100074

近/超临界喷射 RP-3航空煤油 10组分替代物 射流结构 相变

国家两机专项先进航空动力创新项目南京航空航天大学研究生科研与实践创新计划南京航空航天大学研究生科研与实践创新计划

2017-Ⅲ-0007-0033HKCX2020-02-020xcxjh20210206xcxjh20210210

2024

10.13224/j.cnki.jasp.20220614

航空动力学报
中国航空学会

航空动力学报

CSTPCD北大核心
影响因子：0.59
ISSN：1000-8055
年,卷(期)：2024.39(8)
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