Experiment on longitudinal combustion instability of a hypergolic propellant model engine
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摘要:
基于自燃推进剂液/液双旋流喷嘴，设计多喷嘴模型火箭发动机，通过试验研究了氧燃比、缩进长度对自燃推进剂模型火箭发动机高频纵向燃烧不稳定的影响。结果表明：在0.4 mm缩进时，2阶纵向模态会出现“分频”现象，而该现象在更大缩进长度时不会发生，推测该现象与液/液双旋流喷嘴内、外锥形液膜间撞击波动导致的释热波动有关。随着缩进长度的增大，模型发动机纵向燃烧不稳定减弱，这与燃烧释热区域向缩进室内移动，导致其抵抗燃烧室压力扰动能力增强有关。在设计流量下，增大氧燃比使得模型发动机纵向燃烧不稳定减弱，但仍有从1阶纵向模态主导向2阶纵向模态主导过渡的趋势，即2阶纵向模态振荡幅值超过1阶纵向模态振荡幅值；在推进剂总流量偏离设计流量−14%的工况下，增大氧燃比使得2阶纵向模态显著增强，1阶纵向模态会显著减弱。
Abstract:Based on dual-liquid swirl coaxial injectors of hypergolic propellant, a multi-injector model rocket engine was designed to study the effects of oxygen-fuel ratio and recess length on high-frequency longitudinal combustion instability. The results showed that there was a frequency division phenomenon in second-order longitudinal mode when recess length was 0.4 mm, while this phenomenon did not occur with a larger recess length. It was inferred that the frequency division phenomenon was related to the heat release fluctuation caused by the impact fluctuation between the inner and outer conical liquid films of the dual-liquid swirl coaxial injector. With the increase of recess length, the longitudinal combustion instability was also weakened, which was related to the movement of the combustion heat-release region towards the recess chamber, resulting in an enhancement to resist pressure disturbances in the combustion chamber. The increase of oxygen-fuel ratio weakened the longitudinal combustion instability of the model engine under the designed flow rate, while there was still a trend of transition from the first-order longitudinal mode dominant to the second-order longitudinal mode dominant, namely, the amplitude of the second-order longitudinal mode oscillation exceeded the amplitude of the first-order longitudinal mode oscillation. With the increase of oxygen-fuel ratio, the second-order longitudinal mode was significantly enhanced, and the first-order longitudinal mode was weakened under operating conditions deviating from the designed flow rate by −14%.
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图 1 试验系统示意图和热试车图
Figure 1. Schematic of the experiment system and diagram of the combustor hot-fire test
图 4 Probe 1处高频压力信号的PSD分析（试验3）
Figure 4. PSD of high frequency pressure signal at Probe 1 （test No.3）
图 5 Probe 1处高频压力信号的STFT分析（试验3）
Figure 5. STFT of high frequency pressure signal at Probe 1 （test No.3）
图 6 Probe 1处高频压力信号在不同时间段的PSD分析（试验3）
Figure 6. PSD of high frequency pressure signal over different time periods at Probe 1 （test No.3）
图 7 试验 1～试验 8 高频压力信号的 STFT 分析
Figure 7. STFT of high frequency pressure signal in test No.1— test No.8
图 9 振荡频率和振荡幅值随氧燃比的变化
Figure 9. Variation of vibration frequency and magnitude with γO/F
表 1 试验工况
Table 1. Summary of the experiment conditions
试验编号 Lr/mm $ \dot{{m}_{{\mathrm{f}}}} $/（g/s） $ \dot{{m}_{{\mathrm{O}}}} $/（g/s） γO/F pc/MPa 1 0.4 111 187 1.685 0.76 2 0.4 120 186 1.550 0.78 3 0.4 137 221 1.613 0.91 4 0.4 117 246 2.103 0.98 5 1 136 214 1.574 0.90 6 1 85 253 2.976 0.84 7 2 138 227 1.645 0.93 8 2 123 247 2.006 0.98 
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表 2 不同时间段内不同频段的平均功率
Table 2. Average power in different frequency bands over different time periods
时间/s PF1/10−6 MPa2 PF2/10−6 MPa2 S/10−6 MPa2 0.5～1 2.59 8.68 11.27 1～1.5 6.30 5.24 11.54 S0.5～1 s/S1～1.5 s 0.977
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