不同设计参数对变几何涡轮气动性能的影响

徐明林; 张彬滨; 刘政沅; 王彧; 周波

doi:10.13224/j.cnki.jasp.20230192

不同设计参数对变几何涡轮气动性能的影响

doi: 10.13224/j.cnki.jasp.20230192

徐明林^1,,
张彬滨¹,
刘政沅¹,
王彧^{1, 2},
周波^1,*, ,

1.
大连理工大学船舶工程学院工业装备结构分析国家重点实验室，辽宁大连 116024
2.
中远海运重工有限公司技术中心，辽宁大连 116113

基金项目: 国家自然科学基金面上项目（52071059）

详细信息

作者简介:
徐明林（1998-），男，硕士生，主要从事流体机械的数值仿真研究。E-mail：2389868029@qq.com

通讯作者:
周波（1977-），男，教授，博士，主要从事海洋工程应用装备研发等相关方面的研究工作。E-mail：bozhou@dlut.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2023-03-28
- 网络出版日期: 2024-03-27

Influences of different design parameters on aerodynamic performance of variable geometry turbine

XU Minglin^1
,,
ZHANG Binbin¹,
LIU Zhengyuan¹,
WANG Yu^{1, 2},
ZHOU Bo^{1,*
, ,}

1.
State Key Laboratory of Structural Analysis for Industrial Equipment，School of Naval Architecture and Ocean Engineering，Dalian University of Technology，Dalian Liaoning 116024，China
2.
Technical Center，COSCO Shipping Heavy Industry Company Limitd，Dalian Liaoning 116113，China

摘要

摘要:
为了探索提高变几何涡轮效率的可能性，采用数值模拟方法研究了转子速度为2700 r/min，导叶转动角为−5.0°、−2.5°、0°、+2.5°和+5.0°时，枢轴直径系数、枢轴截面形状、端部间隙以及动导叶间距对涡轮气动性能的影响。并针对等熵效率对上述设计参数的敏感性以及流场机理展开分析。研究结果表明：直径系数D/L每增加1.0%，等熵效率能够提升0.064%。菱形枢轴对涡轮效率的提升效果最佳，在各个导叶转动角下，效率提升均在0.8%以上。端部间隙是涡轮效率最敏感的影响参数，当端部间隙从0.5%增加到1.0%跨距时，等熵效率最小降低2.08%，最大为4.54%。增加动导叶间距能够一定程度提高涡轮性能，减小间距对提升涡轮效率不利。选取合适的设计参数能够有效提升低转速下变几何涡轮的工作效率。
- 变几何涡轮 /
- 等熵效率 /
- 导叶转动角 /
- 设计参数 /
- 气动性能 /
- 敏感性
Abstract:
To explore the possibility of improving the efficiency of variable geometry turbines, the effects of the pivot diameter coefficient, pivot cross-sectional shape, end clearance, and spacing between stator and rotor on turbine aerodynamic performance were investigated by numerical simulation at rotor speed of 2700 r/min and guide vane rotation angles of −5.0°, −2.5°, 0°, +2.5°, and +5.0°. And the sensitivity of isentropic efficiency to the above design parameters and the field mechanism were analyzed. The results showed that the isentropic efficiency could be improved by 0.064% for each 1.0% increase in the diameter coefficient D/L. The rhombic section had the best improvement in turbine efficiency, and the isentropic efficiency improvement was above 0.8% at different guide vane rotation angles. The end clearance was the most sensitive parameter to the turbine efficiency. When the end clearance increased from 0.5% to 1.0% span, the isentropic efficiency decreased by a minimum of 2.08% and a maximum of 4.54%. Increasing the spacing between the stator and rotor could improve the turbine performance to some extent, and decreasing the spacing was detrimental to turbine efficiency. Suitable design parameters can effectively improve the efficiency of variable geometry turbines at low speeds.
- variable geometry turbine /
- isentropic efficiency /
- guide vane rotation angles /
- design parameters /
- aerodynamic performance /
- sensitivity

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图 1 1.5级变几何涡轮的子午流道

Figure 1. Meridian flow passage of 1.5-stage variable geometry turbine

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图 2 网格划分

Figure 2. Meshing

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图 3 S1出口处α分布

Figure 3. Distribution of α at the outlet of S1

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图 4 S1出口处马赫数分布

Figure 4. Distribution of Mach number at the outlet of S1

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图 5 不同D/L质量流量曲线

Figure 5. Mass flow at different D/L

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图 6 不同D/L等熵效率曲线

Figure 6. Isentropic efficiency at different D/L

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图 7 不同D/L下S1出口α分布

Figure 7. Distribution of α at outlet of S1 at different D/L

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图 8 不同D/L下S1出口总压损失分布

Figure 8. Distribution of total pressure loss at outlet of S1 at different D/L

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图 9 不同导叶开度下等熵效率随D/L变化

Figure 9. Variation of isentropic efficiency with D/L at different β

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图 10 枢轴截面形状

Figure 10. Pivot cross-sectional shapes

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图 11 不同枢轴形状质量流量曲线

Figure 11. Mass flow at different pivot shapes

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图 12 不同枢轴形状等熵效率曲线

Figure 12. Isentropic efficiency at different pivot shapes

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图 13 圆形和菱形枢轴叶顶相对马赫数和流线分布

Figure 13. Distribution of relative Mach numbers and streamlines at the tip of circular and rhombic pivot

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图 14 圆形和菱形枢轴叶顶表面静压分布

Figure 14. Distribution of static pressure at tip of circular and rhombic pivot

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图 15 圆形和菱形枢轴S1出口处的总压损失

Figure 15. Distribution of total pressure loss at the outlet of S1 of circular and rhombic pivot

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图 16 不同导叶开度等熵效率随枢轴形状变化

Figure 16. Variation of isentropic efficiency with pivot shape at different β

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图 17 不同端部间隙质量流量曲线

Figure 17. Mass flow at different end clearances

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图 18 不同端部间隙等熵效率曲线

Figure 18. Isentropic efficiency at different end clearances

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图 19 不同端部间隙下S1 出口绝对气流角分布

Figure 19. Distribution of α at S1 outlet at different clearances

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图 20 不同端部间隙下S1出口总压损失分布

Figure 20. Distribution of ω at S1 outlet of at different clearances

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图 21 不同端部间隙下S1出口总压损失云图

Figure 21. Cloud diagram of total pressure loss at the outlet of S1 at different clearances

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图 22 不同开度下等熵效率随端部间隙变化

Figure 22. Variation of isentropic efficiency with end clearances at different β

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图 23 不同动导叶间距质量流量曲线

Figure 23. Mass flow at different spacing between stator and rotor

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图 24 不同动导叶间距等熵效率

Figure 24. Isentropic efficiency at different spacing between stator and rotor

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图 25 不同动导叶间距 R1出口马赫数分布

Figure 25. Distribution of Mach number at the outlet of R1 at different spacing between stator and rotor

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图 26 不同动导叶间距 R1出口总压损失分布

Figure 26. Distribution of total pressure loss at the outlet of R1 at different spacing between stator and rotor

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图 27 不同开度下等熵效率随动导叶间距变化

Figure 27. Variation of isentropic efficiency with spacing between stator and rotor at different β

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D/mm	枢轴直径	V_m/（m/s）	速度在轴向上的分量
L/mm	叶片弦长	V_t/（m/s）	速度在切向上的分量
A/mm	叶片轴向弦长	ω	总压损失
$\gamma $/（°）	交错角	p_1t/Pa	进口总压
h/mm	叶片跨距	p_t/Pa	当地总压
$\tau $/mm	端部间隙	p_2t/Pa	出口总压
x/mm	动叶移动距离	p₂/Pa	出口静压
$ \dot{m} $/（kg/s）	质量流量	H_i/J	入口焓
$\eta $	等熵效率	H_o/J	实际情况的出口焓
$\alpha $/（°）	出口绝对气流角	H_os/J	完全恒熵情况的出口焓
$\beta $/（°）	导叶转动角

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表 1 1.5级变几何涡轮叶片几何参数

Table 1. Geometric parameters of 1.5-stage variable geometry turbine blades

参数	S1	R1	S2
L/mm	80.88	59.72	85.50
A/mm	49.71	46.83	72.04
γ/（°）	50.2	35.5	30.9
h/mm	70	70	70
$ \tau $/mm	0.7	0.7	0

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表 2 网格无关性验证

Table 2. Mesh independence verification

参数	$\dot m $/（kg/s）	$\dot m $误差/%	$ \eta $	η误差/%
试验^[19]	11.70		0.91
网格数132万	11.3952	−2.605	0.9001	−1.087
网格数372万	11.4616	−2.037	0.9039	−0.668
网格数745万	11.4609	−2.044	0.9075	−0.274

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