Effects of oxygen-fuel ratio on combustion stability of a model rocket engine with hypergolic propellant
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摘要:
为研究氧燃比（O/F）对自燃推进剂模型火箭发动机燃烧稳定性的影响，在液/液双旋流矩形模型发动机中开展不同氧燃比条件下的试验，采用高频压力传感器和光电倍增管（PMT）同步捕捉了燃烧室压力振荡和CH*表征的释热脉动，获得了氧燃比对燃烧稳定性的影响规律。结果表明：点火后燃料集液腔出现了41 Hz的低频脉动，并在关机过程中诱发了燃烧室同步低频振荡。氧燃比从0.933～1.789增长的过程中，燃烧室经历了稳定、轻微不稳定、一阶横向不稳定和二阶横向不稳定的转换过程，在二阶模态下压力振荡幅值仅为平均室压的4.69%。结合光电倍增管信号，发现燃烧不稳定越剧烈压力和释热信号的耦合就越明显。基于试验的瑞利指数分析表明：一阶横向模态下燃烧不稳定的驱动源主要位于燃烧室两侧，燃烧室中间则呈抑制特性；燃烧不稳定的产生可能和推进剂与燃烧室壁面的相互作用有关。
Abstract:To estimate the effects of oxygen-fuel (O/F) ratio on the combustion stability of a model rocket engine with hypergolic propellant, experiments were carried out at different O/F ratios in a rectangular model engine with dual-liquid swirl coaxial injectors. The pressure oscillations and CH*-characterized heat release pulsations in the combustion chamber were simultaneously recorded by high-frequency pressure sensors and photomultiplier tubes (PMT). The effects of O/F ratio on combustion stability were obtained. The results show that the low-frequency oscillation of 41 Hz occurs in fuel mainfold after combustion initiation, which induces synchronous low-frequency oscillations in the combustion chamber during shutdown. In the process of increasing O/F ratio from 0.933 to 1.789, the combustion chamber undergoes a combustion stability transition process of stability, mild instability, first-order transverse instability, and second-order transverse instability. The amplitude of pressure oscillations in the 2W mode is only 4.69% of the mean combustion chamber pressure. By incorporating the PMT signal, it is found that the coupling of pressure and heat release signals is more obvious when combustion instability is more intense. Rayleigh index analysis based on the experimental data shows that the driving source of combustion instability in the 1W mode is mainly located at both sides of the combustion chamber, while suppression is found in the middle of the combustion chamber. The analysis suggests that the generation of combustion instability may be related to the interaction between the propellant and the combustion chamber walls.
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图 1 模型发动机试验系统及热试车
Figure 1. Schematic of the model engine experiment system and diagram of hot-fire test
图 2 模型发动机诊断装置和关键尺寸
Figure 2. Configuration of model engine diagnostic sensors and key geometric parameters
图 5 Probe 1监测点热试车压力振荡细节（Test 3）
Figure 5. Detailed pressure oscillations of Probe 1 during hot-fire Test 3
图 7 氧燃比对压力振荡模态和幅值的影响（Test 2～Test 5, Probe 1）
Figure 7. Effects of O/F ratio on mode and amplitude of pressure oscillation at Probe 1 in Test 2～Test 5
图 9 压力和CH*发光强度振荡特性和PMT信号PSD分析
Figure 9. Pressure and CH* luminescence intensity oscillations and PSD analysis of PMT signals
图 10 Test 3 PMT信号振荡特性及瑞利指数分布
Figure 10. Pulsation of PMT signals and distribution of Rayleigh index of test 3
表 1 试验结果总结
Table 1. Summary of experimental results
试验
编号$ \mathop {\dot m}\nolimits_{\mathrm{F}} /\left({\mathrm{g}} \cdot {{\mathrm{s}}^{ - 1}} \right)$ $ \mathop {\dot m}\nolimits_{\mathrm{O}} /\left({\mathrm{g}} \cdot {{\mathrm{s}}^{ - 1}} \right)$ Pc/MPa O/F $ \left(\dfrac{P'}{P_{\mathrm{c}}}\right)\bigg/ $% f /Hz 结果 1 231.5 216.1 0.73 0.933 5.62 1981 稳定 2 188.7 248.8 0.75 1.318 7.85 2363 轻微 3 183.8 270.0 0.80 1.469 12.42 2381 1W模态 4 181.3 291.5 0.82 1.608 4.88 2409 1W-2W模态 5 173.6 310.5 0.86 1.789 4.69 4628 2W模态 
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