Supersonic Combustion Using a Stinger-Shaped Fuel Injector
Supersonic Combustion Using a Stinger-Shaped Fuel Injector
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DOI：
10.2514/1.b34524
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发表时间：
2013-05
影响因子：
1.9
通讯作者：
T. Kouchi;G. Masuya;K. Hirano;A. Matsuo;S. Tomioka
中科院分区：
文献类型：
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作者：
T. Kouchi;G. Masuya;K. Hirano;A. Matsuo;S. Tomioka
作者研制了一种用于超声速燃烧室冷流试验的针形引射器（针形引射器）。托管架引射器具有在流向狭缝前面具有尖锐前缘的端口几何形状。这种喷射器产生较高的射流穿透在较低的射流横流动量通量比J比传统的圆形喷射器。在马赫数为2.44、驻点温度为2060 K的条件下进行了燃烧试验。在低燃料当量比Φ状态（即，低J状态）时，由于冷流实验所预期的高射流穿透，喷射器产生的压力推力比圆形喷射器高10%。即使在中等的Φ区域，托管架喷射器也比圆形喷射器产生更高的压力推力。在中等Φ时，尾喷管将火焰保持在喷注器周围，并在喷注器前方产生预燃激波。预燃激波的存在降低了横流空气的动量通量，减小了燃烧室的温度。
The authors developed a stinger-shaped injector (stinger injector) for supersonic combustors in cold-flow experiments. The stinger injector has a port geometry with a sharp leading edge in front of a streamwise slit. This injector produced higher jet penetration at a lower jet-to-crossflow momentum flux ratio J than a conventional circular injector. We applied the injector in a Mach 2.44 combustion test at a stagnation temperature of 2060 K. At a low fuel-equivalence ratio Φ regime (i.e., low J regime), the injector produced 10% higher pressure thrust than the circular injector because of high jet penetration as expected from the cold-flow experiments. Even at a moderate Φ regime, the stinger injector produced higher pressure thrust than the circular injector. At moderate Φ, the stinger injector held the flame around the injector and generated a precombustion shock wave in front of the injector. The presence of the precombustion shock wave decreased the momentum flux of the crossflow air and diminished th...