Rotating Detonation Combustion Characteristics of Kerosene-Fueled Wide-Area Scramjets
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摘要: 通过三维数值仿真的方法, 研究了Ma＝3~7飞行工况下, 煤油燃料冲压旋转爆震燃烧特性。在Ma＝3飞行工况下, 由于燃料雾化蒸发效果较差, 无法实现煤油燃料的爆震燃烧。Ma＝4, 5, 6的飞行工况下, 随着飞行Mach数的增大, 波头数目整体上逐渐增多, 分别为单波、三波、五波模态; 但传播速度逐渐减小; 冲压模态下, 液态燃料雾化蒸发效果较好, 但流场内均不同程度地残存有煤油蒸气, 其未参加反应便排出燃烧室。Ma＝7的飞行工况下, 由于来流接近CJ速度, 流场将以驻定爆震模态组织燃烧。Abstract: Through the method of three-dimensional numerical simulation, the rotating detonation combustion characteristics of kerosene-fueled scramjets in the range of Ma＝3~7 were studied. In the flight condition of Ma=3, due to the poor effect of fuel atomization and evaporation, the detonation combustion of kerosene fuel cannot be realized. In the flight conditions of Ma＝4, 5, 6, with the increase of Mach number, the number of wave heads increases gradually, which are single-wave, three-wave, and five-wave modes, respectively. However, the propagation speed gradually decreases. In the scramjet mode, the liquid fuel has a good effect of atomization and evaporation. Nevertheless, kerosene vapor remains in the flow field to varying degrees and is discharged from the combustion chamber without participating in the reaction. In the flight condition of Ma＝7, the flow field will burn in a stationary detonation mode because the incoming flow is close to CJ velocity.
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Key words:
- kerosene /
- wide-area scramjet /
- rotating detonation /
- combustion characteristics
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图 1 冲压旋转爆震环形燃烧室示意图
Figure 1. Annular combustion chamber for scramjet rotating detonation
图 3 Ma=3, H=15 km飞行工况下煤油燃料冲压旋转爆震解耦云图
Figure 3. Decoupled contour for rotating detonation combustion of kerosene-fueled scramjet at Ma=3, H=15 km
图 4 Ma=4, H=20 km飞行工况下三维环形燃烧室内流场云图
Figure 4. Contour of flow field in a three-dimensional annular combustion chamber at Ma=4, H=20 km
图 5 X=105 mm，Y=0 mm，Z=-60 mm处监测点压力、温度随时间变化图
Figure 5. Pressure and temperature curves with time at the monitoring point at X=105 mm, Y=0 mm, Z=-60 mm
图 7 燃烧室内燃油粒径及爆震波头压力等值面
Figure 7. Fuel particle size and pressure iso-surface of detonation wave head in combustion chamber
图 8 稳定传播阶段粒径分布统计
Figure 8. Particle size distribution statistics in stable propagation stage
图 9 Ma=5, H=24 km飞行工况下流场云图
Figure 9. Contours of flow field in a three-dimensional annular combustion chamber at Ma=5, H=24 km
图 10 X=105 mm, Y=0 mm, Z=120 mm监测点处的压力及温度随时间变化曲线
Figure 10. Pressure and temperature curves with time at the monitoring point at X=105 mm, Y=0 mm, Z=120 mm
图 12 环形燃烧室内燃油粒径及爆震波头等值面
Figure 12. Fuel particle size and pressure iso-surface of detonation wave head in annular combustion chamber
图 14 Ma=6, H=28 km飞行工况下三维环形燃烧室内流场云图
Figure 14. Contour of flow field in a three-dimensional annular combustion chamber at Ma=6, H=28 km
图 15 X=105 mm, Y=0 mm, Z=110 mm监测点处的压力及温度随时间变化曲线
Figure 15. Pressure and temperature curves with time at the monitoring point at X=105 mm, Y=0 mm, Z=110 mm
图 16 环形燃烧室二维环面展开图
Figure 16. Two-dimensional annular expansion diagram of annular combustion chamber
图 17 燃料粒径分布及爆震波头压力等值面
Figure 17. Fuel particle size and pressure iso-surface of detonation wave head in annular combustion chamber
图 19 Ma＝7, H=30 km飞行工况时R=105 mm处环面
Figure 19. Annular flow fields at R=105 mm in flight condition of Ma=7, H=30 km
图 20 燃烧室内燃料液滴分布及驻定爆震波头分布
Figure 20. Fuel droplet and stationary detonation wave head in combustion chamber
表 1 化学反应方程式及参数
Table 1. Chemical reaction equations and parameters
reaction equation A E/(J/(kg·mol)) C12H23+17.75O2=12CO2+11.5H2O 2.58×109 1.25×108 
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表 2 Ma＝3~7飞行工况下隔离段入口条件
Table 2. Entrance conditions of isolation section at Ma=3~7
H/km Ma Pin/kPa Tin/K Main P0/kPa Ps/kPa Ts/K Pout/kPa 15 3 442.51 606.69 1.5 252.23 68.71 418.41 12.05 20 4 831.31 909.0 2 415.65 53.12 505.0 5.46 24 5 1 550.62 1 323.1 2.5 697.78 40.84 588.04 2.93 28 6 2 504.56 1 841.1 3 1 001.83 27.27 657.54 1.586 30 7 4 847.74 2 426.2 3.5 1 696.709 22.25 703.25 1.17
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