Evolution and loss mechanism of tip leakage flow in transonic compressor under gas-solid two-phase conditions
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摘要:
为深入揭示气固两相工况下压气机叶尖间隙泄漏涡结构的动态演化规律及其性能影响机制，基于分离涡模拟（DES）与离散相模型（DPM），利用 Fluent 软件对 Rotor37 跨声速压气机开展了单相和气固两相工况下的数值模拟研究。采用 Omega 涡识别准则对叶尖间隙泄漏涡结构进行识别，采用熵产率作为压气机流动损失表征参数。研究结果表明：相较于单相工况，气固两相工况下压气机叶片 90% 叶高截面流道内超声速区域显著收窄，激波位置提前，且激波前缘出现减速过渡区；通过 Omega 准则对两种工况下叶尖泄漏涡结构的识别，发现颗粒相显著促进了涡旋结构的脱落与重组；通过观察压气机叶片上各位置熵产率变化，显示颗粒相的存在显著增大了压气机流动损失，并且降低了压气机的增压能力和等熵效率。
Abstract:To gain in-depth insights into the dynamic evolution law of the tip clearance leakage vortex structure in a compressor and its impact on performance under gas-solid two-phase conditions, numerical simulations were carried out on the Rotor37 transonic compressor under both single-phase and gas-solid two-phase operating conditions using Fluent software, based on the Detached Eddy Simulation DES (DES)-Discrete Phase Model (DPM) coupling model. The Omega vortex identification criterion was adopted to identify the tip clearance leakage vortex structure, and the entropy production rate was utilized as the characteristic parameter for quantifying the compressor’s flow losses. Results demonstrated that, compared with the single-phase condition, the supersonic region in the flow passage at the 90% blade height section of the compressor blade was significantly narrowed under the gas-solid two-phase condition, the shock wave position shifted upstream, and a deceleration transition zone appeared at the leading edge of the shock wave. Moreover, identification of the tip leakage vortex structures under the two operating conditions via the Omega criterion revealed that the particle phase significantly promoted the shedding and reorganization of the vortex structures. Additionally, observations of the variations in entropy production rate at different positions on the compressor blades showed that the presence of the particle phase not only significantly increased the compressor’s flow losses, but also reduced the compressor’s pressurization capacity and isentropic efficiency.
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Key words:
- vortex identification /
- Omega criterion /
- gas-solid two-phase /
- compressor /
- entropy production rate /
- flow loss
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图 4 CFD与实验数据特性曲线对比
Figure 4. Comparison of characteristic curves between CFD and experimental data
图 5 单相、气固两相条件下等熵效率随时间变化趋势
Figure 5. Variation trend of isentropic efficiency with time under single-phase and gas-solid two-phase conditions
图 7 单相、气固两相10t时刻不同叶高展向速度场分布
Figure 7. Distribution of spanwise velocity field at different blade heights for single-phase and gas-solid two-phase at 10t moment
图 8 单相和气固两相吸力面极限流线云图
Figure 8. Limiting streamlines contour on the suction surface for single-phase and gas-solid two-phase
图 9 单相、气固两相工况下不同时刻Omega等值面
Figure 9. Omega isosurfaces at different time instants for single-phase and gas-solid two-phase conditions
图 10 10t时刻10%、90%叶高展向Omega等值面
Figure 10. Omega iso-surfaces at 10% and 90% span at 10t time instant
图 11 距叶根前缘下游1 cm位置轴向截面熵产率云图
Figure 11. Contour plot of entropy generation rate on the axial cross-section located 1 cm downstream from the blade root leading edge
图 12 单相、气固两相熵产率不同截面沿叶片弦长分布云图
Figure 12. Chordwise distribution contours of entropy generation rate on various cross-sections for single-phase and gas-solid two-phase flows.
图 13 单相、气固两相工况下不同叶高熵产率分布云图
Figure 13. Contour plot of entropy generation rate distribution at different spanwise locations for single-phase and gas-solid two-phase conditions.
图 14 单相、气固两相压气机性能曲线
Figure 14. Performance curves for single-phase and gas-solid two-phase conditions.
表 1 NASA Rotor37设计参数
Table 1. NASA Rotor37 Design Parameters
参数 设计值 质量流量/（kg/s） 20.188 等熵效率 0.877 设计转速n/（r/min） 17188.7 叶片数N 36 转子叶尖速度/（m/s） 454.14 总温比 1.270 总压比π 2.106 
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