Direct-connection experimental investigation of an oblique detonation combustor with kerosene fuel internal injection
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摘要:
为了研究碳氢燃料内喷型斜爆震发动机的燃烧组织机理，开展了模拟飞行马赫数为8的斜爆震燃烧室数值模拟和燃烧加热直连试验研究。设计了小尺度斜爆震直连试验件，采用航空煤油作为燃料，利用布置于流道中心区域菱形支板通过4×
Φ 0.3 mm小孔组织燃料喷注雾化，利用R 2 mm强制起爆结构在20°楔面上实现斜爆震起爆和驻定燃烧。采用10步11组分的化学反应机理和雷诺时均N-S方程，对燃料喷注掺混过程和发动机起爆燃烧过程进行了数值仿真。结果表明，液体燃料在274 mm距离内完成了蒸发并与来流完成部分掺混，楔面两侧形成了稳定的斜爆震流场，通过光学测量观测到了火焰位置与形态特征，燃烧区在2.2 s的有效试验窗口内保持稳定，试验结果与数值仿真结果在沿程压力、化学反应区特征上吻合较好。研究结果证明了液体碳氢燃料内喷型斜爆震发动机的技术可行性。Abstract:In order to investigate the combustion mechanism of oblique detonation with hydrocarbon fuel internal injection, numerical simulations and direct-connected combustion heating experiments were conducted on an oblique detonation combustor simulating a flight Mach number of 8. A small-scale oblique detonation experimental piece was designed and the aviation kerosene was used as the fuel. Fuel injection and atomization was organized through 4×
Φ 0.3 mm holes on a diamond-shaped strut plate positioned in the center of the flow channel. AnR 2 mm bump was utilized to initialize detonation and stationary combustion on a 20° wedge surface. Numerical simulations of the fuel injection mixing process and engine combustion process were performed using a 10-step, 11-component chemical reaction mechanism, and the Reynolds-averaged Navier-Stokes (RANS) equations. The results indicated that the liquid fuel evaporated within a distance of 274 mm and partially mixed with the high-speed incoming flow. Stable oblique detonation flow fields were formed on both sides of the wedge surface. The flame position and morphological characteristics were observed through optical measurements. The combustion zone remained stable within an effective experimental window of 2.2 s. The experimental results are in good agreement with the numerical simulations in terms of pressure along the flow path and characteristics of the chemical reaction zone. The research findings demonstrate the technical feasibility of internal-injection hydrocarbon fuel-based oblique detonation engines. -
图 1 斜爆震燃烧室结构示意图（单位：mm）
Figure 1. Schematic of the structure of oblique detonation engine prototype （unit：mm）
图 6 压力测量结果及与仿真数据的对比验证
Figure 6. Pressure measurement results and comparison with numerical results
图 8 点火延迟时间、驻留时间与静温沿轴向的变化
Figure 8. Variation of ignition delay time, residence time and static temperature along axial direction
图 9 斜劈楔面局部区域的OH质量分数和数值纹影
Figure 9. OH mass fractions and numerical schlieren of local area of wedge surfaces
图 10 爆震波前后的压力分布
Figure 10. Pressure distribution before and after the oblique detonation wave
图 11 加热器室压、试验背压、供油压力、燃油流量的变化曲线
Figure 11. Variation of heater chamber pressure, experimental back pressure, fuel pressure and fuel mass flow rate
图 12 高速摄影的单色火焰图像与低速摄影的彩色火焰图像
Figure 12. Monochrome flame images by high-speed imaging and color flame images by low-speed imaging
图 13 仿真与试验的火焰形态对比
Figure 13. Comparison of flame morphology between simulation and experiment
表 1 试验及仿真工况
Table 1. Experimental and simulation conditions
pc/MPa ṁa/（g/s） ṁf/（g/s） pb/kPa 5.3 466 8 60 
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