Numerical comparative analysis of suppression effect of nozzlebaffle and regenerative cooling fin baffle on high-frequency unstable combustion
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摘要:
基于三维URANS（unsteady reynolds-averaged Navier-Stokes）模型对全尺寸液氧/煤油火箭发动机高频燃烧不稳定开展了仿真计算。研究了3种隔板对高频切向燃烧不稳定的抑制效果，发现当隔板长度为30 mm时，喷嘴式隔板能有效抑制燃烧不稳定，而两种再生冷却肋片隔板未能完全抑制燃烧不稳定，增加隔板长度到50 mm后，燃烧趋于稳定。结果表明：较短隔板不能完全包络化学反应区域，推进剂纵向分布变化对燃烧不稳定的抑制作用相对较小；隔板增长后，能有效分割燃烧室头部化学反应区域，提升了燃烧稳定性裕度；喷嘴式隔板能抑制切向燃烧不稳定的机理在于隔板喷嘴壁面上存在一个大黏性、大剪切力的黏性影响区。研究结果可为液体火箭发动机隔板设计提供一定指导。
Abstract:Based on the 3D URANS （unsteady reynolds-averaged Navier-Stokes） model, the high-frequency combustion instability of a full-scale liquid oxygen/kerosene rocket engine was simulated. The suppression effects of three kinds of baffles on high frequency tangential combustion instability were studied. When the length of baffles was 30 mm, the nozzle baffle can effectively suppress the combustion instability, meanwhile regenerative cooling fin baffles cannot completely suppress the combustion instability. After increasing the length of baffles to 50 mm, the combustion became stable. The results showed that the short baffle cannot completely envelop the chemical reaction area, and the longitudinal distribution of propellant had relatively little inhibitory effect on the combustion instability. After the length of baffles was increased, it can effectively divide the chemical reaction area at the head of the combustion chamber, which improved the combustion stability margin. The mechanism for the nozzle baffle to suppress the tangential combustion instability is that there is a viscous influence zone with large viscosity and large shear force on the nozzle wall of the baffle. Research results can provide some guidance for the design of baffles in the liquid rocket engine.
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图 3 燃烧不稳定4个阶段压力-释热振荡关系
Figure 3. Pressure-heat release oscillation of unstable combustion in four-stage
图 5 半个周期内截面x=15 mm上的流场参数变化云图
Figure 5. Cloud map of flow field parameter change on section x=15 mm in half cycle
图 7 Case 1、case 4和case 5的压力变化过程
Figure 7. Pressure change history of case 1, case 4 and case 5
图 10 Case 4、case 5在轴向截面反应释热分布
Figure 10. Heat release distribution of case 4 and case 5 in axial section
图 11 Case 1在x=15 mm截面的切向速度分布云图
Figure 11. Tangential velocity distribution cloud diagram of case 1 on x=15 mm section
图 12 隔板喷嘴壁面湍流动能耗散率分布及局部放大图
Figure 12. Distribution of turbulent kinetic energy dissipation rate on the wall of the baffle nozzle and partial magnification
表 1 全尺寸发动机网格边界条件
Table 1. Full-scale engine mesh boundary conditions
编号 名称 边界条件 1 喷嘴 质量流量入口 2 喷注面板 无滑移绝热壁面 3 发动机侧壁面 无滑移绝热壁面 4 喷管出口 压力出口 
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表 2 5个算例下的隔板类型和长度
Table 2. Baffle type and length for five studies
算例 隔板类型 隔板长度/mm Case 1 Baffle 1 30 Case 2 Baffle 2 30 Case 3 Baffle 3 30 Case 4 Baffle 2 50 Case 5 Baffle 3 50
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表 3 Case 2和case 3计算结果对比
Table 3. Comparison of results between case 2 and case 3
算例 压力振幅
Δp/MPa压力振幅占比
平均室压(Δp/p)/%振荡主频
f0/HzCase 2 5.69 43.2 3420 Case 3 5.78 43.9 3475
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