航空学报2025，Vol.46Issue(2)：145-158,14.DOI:10.7527/S1000-6893.2024.30621
基于自激扫掠喷嘴的加力燃烧效率试验
Experiment on afterburner combustion efficiency based on self-excited sweeping nozzle
摘要
Abstract
To prove the feasibility of applying the self-excited sweeping nozzle in the afterburner,and the effective-ness of high frequency dynamic sweeping fuel injection methods for improving the efficiency of afterburner combustion,this study designed a fuel spray bar integrated with the self-excited sweeping nozzles,tested its basic working charac-teristics,such as flow rate,frequency and sweeping angle,and further compared these characteristics with the plain-orifice spray bar.Then,based on the rectangular afterburner test rig,under the same test conditions and the fuel-to-air ratio range,the overall combustion efficiencies are tested and the dynamic wall pressure pulsation information is monitored,employing the plain-orifice spray bar and self-excited sweeping spray bar respectively.The results show that multiple self-sweeping nozzles can be integrated into the spray bar with the diameter limitation of 10mm.the flow capability of the self-excited sweeping spray bar is increased by 23%,compared to the plain-orifice spray bar with the equivalent geometric flow area.For the nozzles in the same spray bar,their operating frequency and sweeping angle responses to the pressure drop are basically the same and have good consistency.The afterburner combustion effi-ciency is improved by 3.7%,by employing the self-excited sweeping spray bar,and no dynamic pressure pulsation fre-quency is detected which is the same or close to the operating frequency of self-excited sweeping nozzle,indicating that high frequency dynamic sweeping fuel injection has no direct impact on the flame thermoacoustic oscillation mode and large scale shedding vortex structure downstream the flameholder.关键词
自激扫掠喷嘴/高频动态扫掠喷射/加力燃烧室/振荡频率/压力脉动/流体振荡器Key words
self-excited sweeping nozzle/high frequency dynamic sweeping fuel injection/afterburner/oscillation frequency/dynamic pressure pulsation/fluidic oscillator分类
航空航天引用本文复制引用
王士奇,温泉,贾志刚,程奕鑫,李林,张弛,霍伟业,马梁..基于自激扫掠喷嘴的加力燃烧效率试验[J].航空学报,2025,46(2):145-158,14.基金项目
先进航空动力创新工作站(HKCX2022-01-010) （HKCX2022-01-010）
国家自然科学基金(52306052) Advanced Jet Propulsion Innovation Center(HKCX2022-01-010) （52306052）
National Natural Science Foundation of China(52306052) （52306052）
