叶尖小翼对Stage 37压气机级稳定裕度的影响

钟兢军; 王缘; 赵傲; 吴宛洋

doi:10.13224/j.cnki.jasp.20230349

叶尖小翼对Stage 37压气机级稳定裕度的影响

doi: 10.13224/j.cnki.jasp.20230349

上海海事大学商船学院，上海 201306

基金项目: 国家自然科学基金重点项目（52236005）；航空发动机及燃气轮机基础科学中心重点项目（P2022-B-Ⅱ-007-001）

详细信息

作者简介:
钟兢军（1963-），男，教授，博士，主要从事叶轮机械气动热力学研究。E-mail：zhongjj@shmtu.edu.cn

通讯作者:
吴宛洋（1990-），女，副教授，博士，主要从事叶轮机械气动热力学研究。E-mail：wywu@shmtu.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2023-05-25
- 网络出版日期: 2024-06-24

Effects of tip winglets on the stable operating margin of Stage 37 compressor stage

Merchant Marine College，Shanghai Maritime University，Shanghai 201306，China

摘要

摘要:
为了进一步研究叶尖小翼对跨声速压气机级稳定工作裕度的影响，采用数值方法对NASA Stage 37压气机级加装不同叶尖小翼的效果进行了研究。通过对比原型压气机级与加装叶尖小翼压气机级的流场特性，揭示了压力面叶尖小翼的扩稳机理。研究结果表明：随着压力面小翼宽度增加，压气机级的稳定工作裕度分别提高了7.35%、12.27%、19.49%、12.34%。压力面小翼的扩稳机理在于有效减弱了泄漏涡与激波的干涉程度，改善了转子区域的通流情况，同时减弱了下游静子的吸力面分离，使得静子区域低能流体减少，降低了流动损失。
- 叶尖小翼 /
- Stage 37压气机级 /
- 叶顶泄漏 /
- 稳定工作裕度 /
- 扩稳机理
Abstract:
In order to further investigate the influence of tip winglets on the stable operating margin of a transonic compressor stage, the effects of different tip winglets on NASA Stage 37 compressor stage were studied numerically by comparing the flow field characteristics of the prototype compressor stage to the compressor stage equipped with tip winglets. Additionally, the stability expansion mechanism of the pressure-side tip winglet was revealed. The results showed that with the increase of pressure-side tip winglet width, the stable operating margin increased by 7.35%, 12.27%, 19.49% and 12.34%, respectively. According to the stability expansion mechanism of the pressure-side tip winglet, the interference between the leakage vortex and the shock wave was weakened, the flow condition in the rotor area improved, and the separation on the downstream stator suction-side was reduced. Consequently, both the low-energy fluid and the flow loss in the stator area were diminished.
- tip winglets /
- Stage 37 compressor stage /
- tip leakage flow /
- stable operating margin /
- stability expansion mechanism

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图 1 转子叶尖小翼设计方法

Figure 1. Design of rotor blade tip winglet

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图 3 压力面叶尖小翼示意图

Figure 3. Sketch of pressure-side tip winglet

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图 2 原型叶片示意图

Figure 2. Sketch of original blade

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图 4 吸力面叶尖小翼示意图

Figure 4. Sketch of suction-side tip winglet

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图 5 Stage 37计算网格示意图

Figure 5. Sketch of Stage 37 computational grid

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图 6 叶尖小翼区域网格拓扑示意图

Figure 6. Sketch of tip winglet grid topology

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图 7 Stage 37压气机级网格无关性验证

Figure 7. Grid independence verification of Stage 37

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图 8 Stage 37压气机级数值计算与试验值对比

Figure 8. Comparison of Stage 37 performance between calculation and experiment

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图 9 加装不同宽度压力面叶尖小翼方案的Stage 37级特性曲线

Figure 9. Stage 37 performance map with different pressure-side tip winglets

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图 10 加装不同宽度吸力面叶尖小翼方案的Stage 37级特性曲线

Figure 10. Stage 37 performance map with different suction-side tip winglets

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图 11 不同宽度压力面小翼对Stage 37稳定工作裕度的影响

Figure 11. Influence of pressure-side tip winglets with different widths on Stage 37 stable operating margin

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图 12 压气机转子99%叶高S1流面轴向速度系数云图

Figure 12. Axial velocity coefficient contours of S1 surface at compressor rotor 99% span

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图 13 压气机转子叶顶间隙泄漏流线

Figure 13. Compressor rotor tip clearance leakage streamlines

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图 14 压气机级转子叶片99%叶高静压系数

Figure 14. Static pressure coefficient distribution on rotor blade 99% span

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图 15 叶顶间隙中部泄漏速度沿轴向弦长分布

Figure 15. Tip leakage velocity distribution along with axial chord at the middle of the tip clearance

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图 16 转子出口轴向速度系数沿叶高分布

Figure 16. Axial velocity coefficient of rotor outlet distribution along with blade height

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图 17 S1流面99%叶高熵值云图

Figure 17. Entropy contours on S1 surface at 99% span

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图 18 静子进口气流角沿叶高分布

Figure 18. Air flow angle at stator inlet distribution along with blade height

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图 19 静子进口速度三角形变化示意图

Figure 19. Diagram of velocity triangle variation at stator inlet

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图 20 压气机内部马赫数为0.3的等值面

Figure 20. Isosurface of Mach number of 0.3 inside compressor

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表 1 Stage 37主要设计参数

Table 1. Main design parameters of Stage 37

参数	数值
转子展弦比	1.19
转子叶片数	36
设计转速/（r/min）	17188.7
叶尖切线速度/（m/s）	454.136
叶顶间隙/mm	0.356
静子展弦比	1.26
静子叶片数	46
质量流量/（kg/s）	20.188
设计压比	2.05
轮毂比	0.70

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表 2 压力面叶尖小翼对Stage 37压气机级绝热效率（总压比）的影响

Table 2. Influence of pressure-side tip winglet on adiabatic efficiency （pressure ratio） of Stage 37

参数	各工况点的变化率/%
参数	PW0.5	PW1.0	PW1.5	PW2.0
∆p （PEP）	−0.46	−0.86	−1.44	−1.65
∆η （PEP）	−0.05	−0.15	−0.3	−0.43
∆p （NSP）	−0.16	−0.31	−0.53	−0.7
∆η （NSP）	+0.16	+0.53	+0.55	+0.7

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