Study on combustion and flow characteristics in a rotating detonation combustor
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摘要: 设计了一台爆轰环腔外径100mm、内径80mm、长117 mm的不带有尾喷管的旋转爆轰发动机燃烧室，并进行了实验和数值模拟研究，来了解不同当量比下的燃烧和流动特性。在该燃烧室头部，空气通过60个直径2mm孔轴向喷射，氢气通过2mm宽环缝喷射。氢气和空气最大供给总压分别可达12和10.5MPa。实验发现，当量比大于2时，燃烧发生在燃烧室以外，为爆燃；当量比接近于1时，燃烧室内存在多个反向旋转爆轰波，爆轰波平均速度较低，不超过1000m/s；当量比小于0.58时，仅有一个爆轰波准稳态旋转。在当量比为0.55时，旋转爆轰波传播速度为1274m/s。在当量比为1时，进行了17s无热防护的旋转爆轰发动机实验，未发现燃烧室有明显烧蚀。数值模拟表明在流量为400g/s时，有3个爆轰波同向旋转，外壁面侧传播速度约为1998m/s。Abstract: A rotating detonation combustor with the outer diameter100mm, the inner diameter 80mm and the axial length 117 mm for the detonation channel was designed. There is no exhaust nozzle attached to the combustor. Numerical and experimental studies were carried out to study combustion and flow characteristics under different equivalence ratio conditions. The air flows into the combustor through 60 orifices each with 2mm in diameter, and the hydrogen gas flows into the combustor through an annular channel with 2mm in width. The maximum total pressures of hydrogen and air can be 12 and 10.5MPa, respectively. When the equivalence ratio is greater than 2, deflagration occurs outside the combustor. When the equivalence ratio is close to 1, multiple counter-rotating detonation waves move in the combustor and the average detonation velocities are lower than 1000m/s. When the equivalence ratio is less than 0.58, only one detonation wave rotates. The detonation velocity is 1274m/s for the equivalence ratio 0.55. The rotating detonation engine without cooling ran for 17 seconds at the equivalence ratio 1 and apparent erosion wasn't found. Three detonation waves are co-rotating with velocities 1998m/s near the outer wall for the mass flow rate 400 g/s in the numerical study.
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Key words:
- rotating detonation engines /
- experiments /
- detonation velocity /
- exhaust plume /
- equivalence ratio
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图 2 具有气动塞式喷管的直径6inch的旋转爆轰发动机设备示意图[12]
Figure 2. Diagram of the six inch diameter modular research rotating detonation engine device coupled to an aerospike plug nozzle
图 3 比冲表示的燃料利用率，氢气/空气[12]
Figure 3. Fuel utilization shown as specific impulse,Isp,hydrogen/air
图 6 传感器S2记录的旋转爆轰波压力曲线，氢气和空气流量分别为10 和350g/s
Figure 6. Pressure traces of rotating detonation by S2,where mass flow rates of hydrogen and air are 10 and 350g/s,respectively
图 7 高速摄影拍摄到的旋转爆轰波，50000fps
Figure 7. Rotating detonation events captured by a high speed camera,50000fps
图 8 旋转爆轰发动机尾焰，氢气和空气流量分别为10和350g/s
Figure 8. Exhaust plume of rotating detonation engine,where mass flow rates of hydrogen and air are 10 and 350g/s,respectively
图 9 部分预混燃烧，氢气和空气流量分别为10和72g/s
Figure 9. Partially-premixed combustion,where mass flow rates of hydrogen and air are 10 and 72g/s,respectively
图 10 压力传感器S1和S2采集到的压力曲线，氢气和空气流量分别为10和636g/s
Figure 10. Pressure traces recorded by S1 and S2,where mass flow rates of hydrogen and air are 10 and 636g/s,respectively
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