Effect of tip winglets on stable operating margin of transonic compressor stage
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摘要:
为了揭示叶尖小翼对跨声速压气机级气动性能的影响机制，利用数值方法研究了压气机级转子叶片上加装不同宽度压力面/吸力面叶尖小翼的作用效果和扩稳机制。同时，提出一种更加系统的叶尖小翼结构设计方法以优化叶尖小翼技术在压气机上的应用，使压气机级压比和绝热效率基本保持不变的前提下提升其稳定工作裕度。研究结果表明：随着压力面小翼宽度的增加，压气机级的稳定工作裕度分别增加了6.01%、9.90%、10.76%、11.43%，压力面叶尖小翼改变了转子叶顶气流偏转角，抑制了叶顶泄漏流的产生和泄漏涡破碎，提升了压气机级的流通能力，同时减弱了静子叶片吸力侧的分离损失。
Abstract:In order to reveal the influence mechanism of tip winglet on the aerodynamic performance of the transonic compressor stage, the aerodynamic characteristics and stability expansion mechanism of compressor stage rotors with different width pressure-side/suction-side tip winglets were studied by numerical method. At the same time, a more systematic structural design method of tip winglet was proposed to optimize the application of tip winglet technology in compressor and improve its stable operating margin on the premise that the pressure ratio and adiabatic efficiency of the compressor stage are kept basically unchanged. The results showed that with the increase of pressure-side tip winglet width, the stable operating margin of the compressor stage increased by 6.01%, 9.90%, 10.76% and 11.43%, respectively. The tip winglet changed the rotor tip flow angle, inhibited the generation of the leakage and the break of the leakage vortex at the tip of rotor blades, improved the flow capacity of the passage, and reduced the separation loss of suction-side stator blades.
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图 1 加装压力面叶尖小翼的DMU37压气机级
Figure 1. DMU37 compressor stage with pressure-side tip winglets
图 4 DMU37压气机级计算域及网格结构划分
Figure 4. Computational domain and grid structure of DMU37 compressor stage
图 5 DMU37压气机级试验与数值结果对比
Figure 5. Comparison of DMU37 compressor stage performance between experiment and calculation
图 6 DMU37压气机级网格无关性验证
Figure 6. Grid independence verification of DMU37 compressor stage
图 7 不同压力面叶尖小翼方案的DMU37级特性曲线
Figure 7. DMU37 compressor stage performance map with different pressure-side tip winglets
图 8 不同吸力面叶尖小翼方案的DMU37级特性曲线
Figure 8. DMU37 compressor stage performance map with different suction-side tip winglets
图 9 压力面叶尖小翼对DMU37压气机级绝热效率和压比的影响
Figure 9. Influence of pressure-side tip winglet on adiabatic efficiency and pressure ratio of DMU37 compressor stage
图 10 压力面叶尖小翼对DMU37压气机级稳定工作裕度的影响
Figure 10. Influence of pressure-side tip winglets on DMU37 compressor stage stable operating margin
图 12 压气机级转子叶片99%叶高的静压系数
Figure 12. Static pressure coefficient distribution on rotor blade 99% span
图 17 静子进口叶顶区域速度三角形的变化
Figure 17. Change in velocity triangles at stator exit for tip span region
图 21 静子总压恢复系数沿叶高分布
Figure 21. Radial distribution of stator total pressure recovery coefficient distribution along span
表 1 DMU37压气机级主要几何及结构参数
Table 1. Main geometric and structural parameters of DMU37 compressor stage
参数 数值 转子展弦比 1.17 转子叶片数 36 设计转速/（r/min） 24566.8 叶尖切线速度/（m/s） 452 设计间隙/mm 0.4 静子展弦比 1.26 静子叶片数 46 设计流量/（kg/s） 10 设计压比 2.05 
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