压气机静叶失速与局部缝隙控制

赵文峰; 姜斌; 段昱; 郑群

doi:10.13224/j.cnki.jasp.20220164

压气机静叶失速与局部缝隙控制

doi: 10.13224/j.cnki.jasp.20220164

1.
中国兵器工业集团有限公司航空弹药研究院有限公司，哈尔滨 150030
2.
哈尔滨工程大学动力与能源工程学院，哈尔滨 150001

基金项目: 国家科技重大专项（2017-Ⅱ-0006-0019，2017-Ⅰ-0009-0010)

详细信息

作者简介:
赵文峰（1992-），男，工程师，博士，主要从事叶轮机械气动热力学研究

中图分类号: V239
计量
- 文章访问数: 100
- HTML浏览量: 60
- PDF量: 31
- 被引次数: 0
出版历程
- 收稿日期: 2022-03-29
- 网络出版日期: 2023-10-19

Stator stall and partial clearance control of compressor

1.
Aviation Ammunition Institute Company, Limited, China North Industries Group Corporation Limited, Harbin 150030，China
2.
Collage of Power and Energy Engineering，Harbin Engineering University，Harbin 150001，China

摘要

摘要:
通过对某8级压气机进行数值计算得到了在设计转速下船舶压气机的流场特点与失稳机理。同时以此8级压气机中的前1.5级被作为研究对象探究压气机静叶轮毂静叶局部缝隙对角区失速的影响。结果表明，在设计转速下近失速点流动的不稳定性主要发生在静叶角区，主要原因是静叶角区失速。角区出现闭式分离泡并堵塞流场。1.5级压气机的计算结果表明，设计转速下压气机的失稳原因与8级压气机相同。通过在不同位置设置静叶局部缝隙可以发现，静叶局部缝隙能够有效的拓宽压气机裕度。其中在中间位置的缝隙扩稳效果最好，可以将裕度从22.1%提升为27.2%，最大效率从93.9%下降到93.21%。其他位置间隙所产生泄漏流动量不足，无法完全消除角区失速涡。最佳静叶局部缝隙的位置是在近失速点角区失速涡的涡核处，此时能保证间隙泄漏流动量最大。
- 静叶失速 /
- 局部缝隙 /
- 失速点 /
- 裕度 /
- 泄漏
Abstract:
By numerical calculation of an 8-stage compressor, the characteristics and instability mechanism of marine compressor at design speed were obtained. At the same time, the first 1.5-stage of an 8-stage compressor was chosen to study the influence mechanism of the partial clearance on hub corner stall. The results showed that the flow instability mainly occurred in the hub-corner of stator at the design speed. The main reason is hub corner stall. The closed separation appeared in the corner and block the flow field. The 1.5-stage compressor result showed that the reason for compressor instability at design speed is the same as that of the 8-stage compressor. the partial clearance at different positions can widen effectively the margin. The effect of clearance was best when the clearance was in the middle. The clearance can not only increase the margin from 22.1% to 27.2%, but also cause the minimum loss at the maximum efficiency operation (from 93.9% to 93.21%). The leakage momentum caused by the clearance in other positions was not enough to eliminate the stall vortex in the hub. The optimal clearance was near the vortex core of stall vortex in the hub corner, where the leakage momentum was the maximum.
- stator stall /
- partial clearance /
- stall point /
- margin /
- leakage

HTML

图 1 计算模型

Figure 1. Computational model

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图 2 计算网格

Figure 2. Computational mesh

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图 3 静叶局部缝隙示意图

Figure 3. Partial clearance schemes of stator

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图 4 试验验证

Figure 4. Experimental verification

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图 5 90%H的相对马赫数

Figure 5. Relative Mach number at 90%H

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图 6 前两级叶顶相对马赫数

Figure 6. Relative Mach number at top of the first 2 stages

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图 7 R1近失速点间隙泄漏流

Figure 7. Clearance leakage at near stall point of R1

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图 8 后两级叶顶相对马赫数

Figure 8. Relative Mach number at top of the last 2 stages

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图 9 S8角区极限流线

Figure 9. Limiting streamline of S8 in hub corner

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图 10 动叶叶顶马赫数云图

Figure 10. Mach number contour at top of rotor

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图 11 动叶叶顶相对涡量

Figure 11. Relative vorticity at top of rotor

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图 12 叶顶回流区的速度（100%转速）

Figure 12. Back-flow in the rotor top (100% rotation speed)

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图 13 角区极限流线与静压系数分布（100%转速）

Figure 13. Limiting streamlines and static pressure coefficient contour in hub corner (100% rotation speed)

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图 14 静压系数云图与角区极限流线（5%H）

Figure 14. Static pressure coefficient contour and limiting streamlines in hub corner (5%H)

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图 15 间隙泄漏与二次流的互相作用

Figure 15. The interaction between clearance leakage and secondary flow

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图 16 静叶出口静熵

Figure 16. Static entropy at outlet of stator

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图 17 轴向密流的径向分布

Figure 17. Radial distribution of axial velocity density

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图 18 不同间隙下的压气机特性线

Figure 18. Characteristic lines with different clearances

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表 1 100%转速压气机裕度

Table 1. Compressor margin at 100% rotation speed

项目原型尾缘后部中间前部

裕度/% 22.1 23.01 24.84 27.8 25.16
效率/% 93.90 93.51 93.31 93.21 92.4

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