Experimental analysis on the longitudinal high frequency combustion instability of a single-element model engine
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摘要: 为掌握喷嘴缩进长度和燃烧室长度对气氧/煤油火箭发动机高频燃烧不稳定性的影响规律，设计并开展了单喷嘴模型发动机燃烧实验。实验选用了气液同轴离心式单喷嘴，采用中心供应氧气，液体煤油经切向孔沿轴向旋转进入喷嘴的形式，为测试燃烧稳定性，燃烧室和喷嘴缩进的长度分别作为实验变量，利用高频压力传感器采集数据，基于压力信号对实验结果，尤其是呈现的纵向高频燃烧不稳定性现象进行了细致地研究。结果表明：在本文研究条件下，随着缩进长度的增加，对纵向高频燃烧不稳定性产生阻尼作用，但不会消除纵向高频燃烧不稳定。燃烧室的长度在516和356mm之间存在某个值，使得喷嘴缩进长度对燃烧稳定性影响可以忽略。随着燃烧室长度的增加，一阶纵向声学频率逐渐减小，而幅值逐渐增强。出现这些现象的原因是燃烧过程压力振荡与声波存在相位差。此外，燃烧室长度对纵向高频燃烧不稳定性的影响比缩进长度更明显。Abstract: In order to understand the influence of injector indentation length and combustion chamber length on high frequency combustion instability of oxygen/kerosene rocket engine, the combustion experiment of single-element model engine was designed and carried out. The gas-liquid coaxial centrifugal single-element was used in the experiment. In order to test the combustion stability, the length of the combustion chamber and that of the injector were used as experimental variables, and the data were collected by high frequency pressure sensor, using the central supply of oxygen and the axial rotation of liquid kerosene through the tangential hole into the injector. Based on the pressure signal, the experimental results, especially the longitudinal high frequency combustion instability, are studied in detail. The results show that:under the conditions studied in this paper, with the increase of the indentation length, the longitudinal high frequency combustion instability is damped, but the longitudinal high frequency combustion instability is not eliminated. The length of combustion chamber is between 516mm and 356mm. The effect of the injector indentation length on the combustion stability is negligible. With the increase of combustion chamber length, the first order longitudinal acoustic frequency decreases gradually. These phenomena are due to the phase difference between the combustion pressure oscillation and the acoustic wave. In addition, the influence of the combustion chamber length on longitudinal high frequency combustion instability is more obvious than that of the indentation length.
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图 2 单喷嘴模型发动机几何结构示意图
Figure 2. Geometric structure of single-element model rocket engine
图 4 燃烧室长度676mm，缩进长度0mm时的压力振荡曲线
Figure 4. Pressure oscillation curve of combustion chamber with length of 676mm and indentation length of 0mm
图 7 燃烧室长度676mm时2种缩进长度的频谱图
Figure 7. The spectral diagram of two kinds of indentation length of combustion chamber at 676mm
图 8 燃烧室长度356mm时两种缩进长度的频谱图
Figure 8. The spectral diagram of two kinds of indentation length of combustion chamber at 356mm
表 1 模型发动机实验工况概览
Table 1. Test of engine summary
燃烧室
长度/mm缩进长度
/mm氧气
/(g·s-1)煤油
/(g·s-1)混合比 声速流量计
上下游压力比356 0
12
15100 100 1 0.379
0.368
0.368516 0
12
15100 100 1 0.357
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-676 0
12
15100 100 1 0.379
0.368
0.369
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表 2 不同燃烧室长度一阶声学频率理论值与实验值对比
Table 2. Comparison of theoretical and experimental values of first-order acoustic frequencies with different combustor lengths
燃烧室
长度
/mm氧气
/(g·s-1)煤油
/(g·s-1)一阶声学
频率理论
值/Hz一阶纵向
频率实验
值/Hz理论与
实际值
偏差/%676 100 100 796.0 845 +5.80
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