INVESTIGATION OF SUPERSONIC COMBUSTION ENHANCEMENT USING BARBOTAGE AND INJECTORS WITH NONCIRCULAR NOZZLES
INVESTIGATION OF SUPERSONIC COMBUSTION ENHANCEMENT USING BARBOTAGE AND INJECTORS WITH NONCIRCULAR NOZZLES
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使用Barbotage和非圆形喷嘴喷射器增强超声燃烧的研究
DOI：
10.2514/6.1998-1516
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发表时间：
1998
期刊：
影响因子：
--
通讯作者：
S. A. Zosimov
中科院分区：
文献类型：
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作者：
V. Sabel;K. Schadow;V. Ivanov;O. Voloschenko;S. A. Zosimov
本文介绍了在超燃冲压发动机燃烧室中进行的管道燃烧试验的结果。试验中采用了从管形微塔和翼形微塔中喷出的椭圆形喷管，喷射掺气（氢或空气）/液体煤油（煤油）射流。在二维扩压区超声速燃烧室中，分别采用与主流气流方向成45 °角的微型喷管和翼塔底部喷管两种方式喷入激波射流。在后一种情况下，使用共流注射。试验在入口马赫数M=2.5和总温Tt=1650- 1800 K范围内进行。采用椭圆形喷管的试验结果与采用圆形喷管的基线结果进行了比较。燃烧室壁面上的轴向静压分布和计算的压力-面积积分表明，在从管形微塔喷射时，椭圆形喷嘴的煤油喷雾性能优于圆形喷嘴。椭圆喷管和圆形喷管的燃烧效率没有明显的差别。
The paper presents the results of the ducted combustion test program on the supersonic mixing and combustion enhancement in scramjet combustor using aerated by gas (hydrogen or air) liquid kerosene (effervescent) jets injected through elliptic nozzles from tube-micropylons and fin-pylons. Kerosene jets were injected into two-dimensional diverging-area supersonic combustor in two ways: 1) through nozzles in tube-micropyl ons at an angle of 45 degrees relative to the mainstream air flow direction and 2) through the nozzles located at the base of fin-pylons. In the latter case co-flow injection was used. Tests were conducted at entrance Mach number M=2.5 and total temperature in the range Tt=1650-1800K. The tests results with using elliptic nozzles were compared to baseline results with circular nozzles. The axial static pressure distributions on the combustor walls and calculated pressure-area integrals showed that the effervescent kerosene sprays performed better for elliptic nozzles than for round nozzles at injection from tubemicropylons. Injection from fin-pylons did not show noticeable difference in combustion efficiency for elliptic and round nozzles.