波瓣混合器内扩张角对一体化加力燃烧室性能的影响  

Influence of Lobe Inward Penetration Angle on Performance of Integrated Afterburner

作　　者：杜力伟 DU Li-wei(Research Center of System Engineering, Aero Engine Academy of China, Beijing 101304, China)

机构地区：[1]中国航空发动机研究院系统工程研究中心,北京101304

出　　处：《科学技术与工程》2020年第12期4992-4999,共8页Science Technology and Engineering

摘　　要：通过开源场运算和OpenFOAM中二次开发的数值计算程序对某型一体化加力燃烧室进行了数值仿真研究,并基于仿真结果定量分析了波瓣混合器内扩张角对加力燃烧室气动热力性能的影响。结果表明:随着内扩张角的增大,强化了加力燃烧室中流体的混合效果,但同时也导致了较大的总压能损失。在加力燃烧室出口处,相对于基准环形混合器模型,内扩张角25°模型对应的热混合效率提升了16.2%、总压恢复系数相对下降了0.88%。当内扩张角逐渐增加时,缩小了不考虑与考虑辐射换热时热混合效率的差值,即减弱了辐射换热强化热掺混的效果。A numerical simulation solver was developed at the OpenFOAM platform and the influence of lobe inward penetration angle on the aero-dynamic performance of an integrated afterburner was studied by using this solver.The results show that with the increase of lobe inward penetration angle,both the magnitude of thermal mixing efficiency and total pressure loss are increased.In the outlet cross section of the studied afterburner,as compared with the baseline case,thermal mixing efficiency of the 25°case has increased by 16.2%,while total pressure recovery coefficient has declined by 0.88%.When the lobe inward penetration angle is gradually increased,the difference of the thermal mixing efficiency between the cases with/without thermal radiation is reduced.Thus,the effect of radiative heat transfer on increasing thermal mixing uniformity is reduced.

关 键 词：波瓣内扩张角 一体化加力燃烧室 OPENFOAM 热混合效率 辐射换热 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]