变循环发动机外涵流量随工作模态转换会发生大幅变化,相应的宽范围内外涵道掺混流动对于形成均匀的燃油空间分布带来了挑战。本文对变循环发动机在不同模态下加力燃烧室的燃油分布特性进行了数值仿真,探究了宽范围外涵气流变化对燃油分布的影响规律,并形成了面向多模态加力燃烧室的燃油喷注优化策略。研究结果表明,加力燃烧室混合气体沿径向的速度分量和波瓣混合器诱导产生的流向涡分别是影响燃油径向/周向扩散的关键因素。小涵道比模态下,内涵主导的高温高速流动使得不同区域的燃油扩散速度相对一致;而大涵道比模态下气体径向速度和流向涡分布规律发生明显改变,导致不同区域的燃油扩散速度表现出明显的差异性,影响到燃油分布的均匀程度。在此基础上,提出了适度增加中间位置喷嘴燃油流量的优化策略,结果表明,相比平均分配燃油流量的供应方案,优化后的燃油分布均匀程度最高将提升33.04%。
The flowrate of the extra-cylinder of the variable-cycle engine will change greatly with the transition of the working mode, and the corresponding internal/external contour blending flow brings challenges to the fuel injection scheme of the afterburner. In order to solve this problem, this paper numerically simulates the fuel distribution characteristics of afterburner in variable cycle engine under different modes, explores the influence of wide-range airflow change on fuel distribution, and forms a fuel injec-tion optimization strategy for multi-modal afterburner. The results show that the velocity component of the afterburner mixture along the radial direction and the flow vortex induced by the lobe mixer are the key factors affecting the radial/circumferential diffusion of the fuel, respectively. In the small bypass ratio mode, the connotation-dominated high-temperature and high-speed flow makes the fuel diffusion velocity relatively consistent in a wide range. However, the radial velocity and vortex distribution of the gas change significantly in the large bypass ratio mode, resulting in obvious differences in the fuel diffusion velocity in different regions, which affects the uniformity of fuel distribution. On this basis, an optimization strategy is proposed to moder-ately increase the fuel flow rate of the nozzle at the middle position, and the results show that the uniformity of fuel distribution will be increased by up to 33.04%.
[1]刘红霞.公司变循环发动机的发展[J].航空发动机, 2015, 41(2):93-98
[2]郝旺, 刘永泉, 王占学, 等.美国自适应循环发动机的发展历程[J].推进技术, 2024, 45(6):1-20
[3]Vdoviak J W, Knott P R.Aerodynamic/acoustic per-formance of YJ101/double bypass VCE with co-annular plug nozzle[R]. NASA CR-159869, 1981
[4]张淑荣.气流式雾化喷嘴的特性研究[D]. 大连:大连理工大学, 2006
[5]Assato M, Inceer A A, Moraes L.Performance benefits of a fan on blade–flade–for a variable cycle engine[C]. The congress of the International council of the Aero-nautical sciences, 2022
[6]Xiao H, Zhao S, Li Y, et al.Influence of time-varying flow on dynamic flame characteristics in VCE: Numerical and experimental study[J].Applied Thermal Engineering, 2024, 236(10):121-135
[7]周红, 王占学, 刘增文, 等.可变面积涵道引射器对变循环发动机性能影响[J].航空动力学报, 2016, 31(12):2842-2850
[8]Kamin M, Khare P.Liquid jet in crossflow: Effect of momentum flux ratio on spray and vaporization char-acteristics[C] Turbo Expo: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2019, 58622: V04BT04A053.
[9]熊永恒.钝体稳定器后直射式喷嘴油雾特性研究[D]. 南京: 南京航空航天大学,2020
[10]刘涛.航空煤油雾化特性实验研究[D]. 合肥: 中国科学技术大学,2018
[11]Fei L, Zhao B, He L.Experimental study on spray characteristics of fan nozzle for integrated afterburner in lateral airflow[J].Aerospace Science and Technology,, 2022, 1(130):1-13
[12]Miniero L, Pandey K, Fredrich D, et al.Air-blast atomization and ignition of a kerosene spray in hot vitiated crossflow[J].Combustion and Flame, 2023, 1(256):1-13
[13]Wei L, Longchao X, Chaodi Y, et al.Experimental investigation of the characteristics of direct injection nozzle sprays in an afterburner environment[J].Aerospace Science and Technology, 2025, 1(157):1-16
[14]孔祥壮, 何悟, 郭志辉.非均匀速度来流条件下液体射流喷雾特性[J].航空动力学报, 2022, 37(03):534-544
[15]Yang X, Fan W, Zhang R.Experimental study of the fuel spray and ignition characteristics in an aeroengine afterburner under subatmospheric pressure[J].Aerospace Science and Technology, 2024, 1(144):1-11
[16]Liu Runfu, Li Zhenyao, Zhang Huiliu, Wang Qixing, Huang Yue, You Yancheng.Numerical study of steady flow characteristics of a rear variable-area bypass in-jector with alternating area regulator[J].Chinese Journal of Aeronautics., 2024, 5(37):180-198
[17]翟文辉.多模态燃烧室一体化设计火焰稳定器燃油分布特性研究[D].南京: 南京航空航天大学, 2019.
[18]尚守堂,何小民等.航空发动机加力燃烧室设计[M].北京:科学出版社,2022
[19]陈玉乾.冷气射流对一体化火焰稳定器性能的影响研究[D]. 南京: 南京航空航天大学,2022
[20]刘润富, 黄玥, 李臻曜, 等.波瓣结构后可变面积涵道引射器掺混特性[J].航空动力学报, 2024, 39(08):384-392
[21]Huang G, Chao Li, Chen Xia.Investigations of entrainment characteristics and shear-layer vortices evolution in an axisymmetric rear variable area bypass injector[J].Chinese Journal of Aeronautics, 2022, 35(4):230-244
[22]Shaw V, Elliott P, Boller M.Droplet evaporation of water and fuel jets in low and high temperature subsonic crossflows[J].Experimental Thermal and Fluid Science, 2022, 1(135):1-20
[23]李浪浪.航空发动机加力燃烧室性能数值研究[D].哈尔滨工程大学, 2023.