射流预冷混排涡扇喷气式发动机热力性能分析  

Thermal Performance Analysis of Mass Injection Pre-compressor Cooling of Mixed Flow Turbofan Jet Engine

作　　者：胡可 岳晨[1] 贺鹏宇 严亚芹 HU Ke;YUE Chen;HE Pengyu;YAN Yaqin(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,China,210016)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《热能动力工程》2025年第1期51-58,共8页Journal of Engineering for Thermal Energy and Power

摘　　要：为了探究射流预冷涡扇发动机的热力性能,采用部件法建立了发动机的数学模型,开展了针对设计点处加力燃烧室燃料转化率对预冷效果影响的研究,分析了沿特定飞行轨迹不同来流工况下发动机喷水后的性能变化规律。结果表明:采用进气道喷水冷却能够有效提升发动机性能。在Ma=2.8设计点工况下,燃料转化率增加使燃烧更充分,喷水量为4%,燃料转化率从0.8增加至0.96,比冲由20 057 s增加至22 998 s,耗油率由0.179 kg/(h·N)降低至0.156 kg/(h·N)。在沿飞行轨迹Ma=2~3.2的过程中,射流预冷在Ma=2.4~2.8范围内对推力等整体性能的改善效果最佳。为避免来流空气进入风扇压缩时液滴的干扰,随着Ma的增加,水气比的最大值逐渐增大;当Ma>2.8时,在水气比1%~6%范围内,比冲快速上升,在水气比超过6%后,比冲上升程度减缓;对于Ma=3.2工况,水气比低于2%时,比冲因加力燃烧室燃烧效率的提升而有一定的提升,水气比达4%以后,过量水会影响加力燃烧室燃料的雾化蒸发和掺混,导致燃烧效率降低,比冲下降。To investigate the thermal performance of jet pre-cooling turbofan engines,a mathematical model of the engine was established using the component method.The study on influences of fuel conver-sion rate on the pre-cooling effect of the afterburner at the design point was conducted,and the perform-ance changes of the engine after spraying water under different inflow conditions along a specific flight trajectory were analyzed.The results indicate that using inlet water spray cooling effectively improves en-gine performance.Under the Ma=2.8 design point operating condition,the increase in fuel conversion rate leads to more complete combustion with the water injection rate of 4%.The fuel conversion rate in-creases from 0.8 to 0.96,the specific impulse increases from 20057 s to 22998 s,and the fuel con-sumption rate decreases from 0.179 to 0.156 kg/(h·N).The jet pre-cooling provides the optimal im-provement in thrust and overall performance in the Ma=2.4-2.8 range along the Ma=2-3.2 flight trajectory.To avoid liquid droplets interference when incoming air flowing into the fan for compression,the maximum of water gas ratio is increased gradually with the increasing of Ma.When Ma exceeds 2.8,the specific impulse increases rapidly in the range of 1%-6%water gas ratio,and the degree of in-crease in specific impulse slows down after the water gas ratio exceeds 6%.Under the Ma=3.2 operat-ing condition,at the water gas ratio below 2%,there is a substantial increase in specific impulse due to the improvement of combustion efficiency in the afterburner.After the water gas ratio exceeds 4%,ex-cessive water will affect the atomization,evaporation and mixing of fuel in the afterburner,resulting in a decrease in combustion efficiency and specific impulse.

关 键 词：射流预冷 水气比 燃烧效率 热力性能 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]