高径位供气孔结构对涡轮轮缘密封特性的影响

盖泽鹏; 胡剑平; 赵义祯; 谭逸; 刘振侠; 李澍

doi:10.13224/j.cnki.jasp.20230034

高径位供气孔结构对涡轮轮缘密封特性的影响

doi: 10.13224/j.cnki.jasp.20230034

盖泽鹏¹,
胡剑平^1,*, ,,
赵义祯²,
谭逸¹,
刘振侠¹,
李澍¹

1.
西北工业大学动力与能源学院，西安 710072
2.
中国航发沈阳发动机研究所，沈阳 110015

基金项目: 工业和信息化部专项科研项目（MJ-2018-D-21）；国家科技重大专项（J2019-Ⅲ-0003-0046）

详细信息

作者简介:
盖泽鹏（1997-），男，博士生，主要从事航空发动机空气系统和润滑系统研究

通讯作者:
胡剑平（1984-），男，副教授，博士，主要从事航空发动机空气系统和润滑系统研究。E-mail：hujp@nwpu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2023-01-15
- 网络出版日期: 2024-08-23

Effect of high-radial sealing hole structure on characteristics of turbine rim seal

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
Shenyang Engine Research Institute，Aero Engine Corporation of China，Shenyang 110015，China

摘要

摘要:
为探究涡轮轮缘密封的精细化设计，在径向轮缘密封结构的基础上引入一种高径位供气孔结构并将高位孔作为主要的封严气路，采用经实验验证的非定常雷诺平均（URANS）数值方法，研究了供气孔的周向进气角度和孔的数目对密封腔的封严效率和非定常流动特性的影响规律，分析了供气孔结构对腔内的不稳定性流动结构和燃气入侵程度的影响机理。结果表明：改变供气孔的周向进气角度最优可将封严效率提高10.15%，最差使其降低8.32%。负进气角的供气孔使腔内的非定常效应增强，伴随有更强烈的流体剪切作用，导致Kelvin-Helmholtz不稳定性涡结构尺度增大，燃气入侵程度加剧，封严效率降低；正进气角的供气孔使掺混后流体的相对速度方向更加统一，Kelvin-Helmholtz不稳定性涡结构尺度减小，燃气入侵程度减弱，封严效率提高。增加孔的数目减小了封严气的射流动量，导致腔内Kelvin-Helmholtz不稳定性涡结构尺度增大，加剧了燃气倒灌的深度，使封严效率降低，但高于无供气孔的轮缘密封结构的封严效率。
- 涡轮 /
- 轮缘密封 /
- 燃气入侵 /
- 封严特性 /
- 不稳定性流动 /
- 精细化设计
Abstract:
To investigate the detailed design of turbine rim seal, a high-radial sealing hole structure was presented on the basis of the radial rim seal configuration, and the hole was considered as the main sealing flow path. The effects of circumferential injection angle and the number of holes on the sealing efficiency and unsteady flow characteristics in the wheel-space were studied using the experimentally validated unsteady Reynolds-average Navier-Stokes (URANS) numerical method, and the influence mechanisms of the hole structure on the instability flow structure and the degree of gas ingestion in the wheel-space were analyzed. The results showed that the change of circumferential injection angle of the hole can optimize the sealing efficiency by 10.15%, and also can reduce it by 8.32% in the worst case. Negative injection angle of the hole enhanced the unsteady effect in the wheel-space, accompanied by stronger fluid shear, which led to an increase in the scale of the Kelvin-Helmholtz instability vortex structure, the increase of gas ingestion and decrease of sealing efficiency. Positive injection angle of the hole made the relative velocity direction of the mixed fluid more uniform, which reduced the scale of the Kelvin-Helmholtz instability vortex structure; the degree of gas ingestion was weakened, and the sealing efficiency was improved. Increasing the number of holes reduced the jet momentum of sealing flow, which led to an increase in the scale of the Kelvin-Helmholtz instability vortex structure in the wheel-space, intensified the depth of gas ingestion and also reduced the sealing efficiency, which, however, was higher than that of the rim seal without holes.
- turbine /
- rim seal /
- gas ingestion /
- sealing effectiveness /
- unsteady flow /
- detailed design

HTML

图 1 1.5级涡轮轮缘封严实验台实物图^[44]

1 Mainstream air supply system; 2 Main experimental section;3 Static pressure and CO₂ concentration probes;4 Probes lead integration hole; 5 Exhaust pipe;6 Four-quadrant rectifier; 7 Secondary flow and CO₂ supply piping; 8 Lubricating oil system; 9 Data collection and processing terminal.

Figure 1. Photo of 1.5-stage turbine rim seal test rig components^[44]

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图 2 轮缘密封模型子午面示意图

Figure 2. Schematic diagram of meridian plane for rim seal configuration

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图 3 4种周向进气角度的供气孔结构模型（以整周21个孔为例）

Figure 3. Models of sealing hole structure with four circumferential injection angles （with 21 holes in a full cycle as example）

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图 4 轮缘密封模型的计算网格

Figure 4. Computational grids of rim seal model

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图 5 非定常计算的时间步长敏感性验证

Figure 5. Time step sensitivity verification of unsteady computation

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图 6 数值计算方法的准确性验证

Figure 6. Accuracy verification of numerical computation method

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图 7 密封腔内的封严效率对比

Figure 7. Comparison of sealing efficiency in wheel-space

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图 8 密封腔内封严效率为0.65的等值面

Figure 8. Equivalent surface with sealing efficiency of0.65 in wheel-space

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图 9 密封腔内不同子午面上的封严效率云图

Figure 9. Contours of sealing efficiency at different meridian planes in wheel-space

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图 10 密封腔内不同子午面的封严效率云图和流线图

Figure 10. Sealing efficiency contours and streamlines at different meridian planes in wheel-space

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图 11 密封腔内封严效率和旋转比沿径向的分布

Figure 11. Radial distribution of sealing efficiency and swirl ratio in wheel-space

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图 12 密封腔内监测点的非定常压力波动频谱分析

Figure 12. Fast Fourier transform of pressure at monitoring point in wheel-space

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图 13 密封腔内距静盘1.5 mm截面上的轴向涡量云图和周向涡量云图

Figure 13. Vorticity contours in axial direction and circumferential direction at plane 1.5 mm from static disc in wheel-space

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图 14 密封腔内距静盘1.5 mm截面上的封严效率云图和流线图

Figure 14. Sealing efficiency contours and streamlines at plane 1.5 mm from static disc in wheel-space

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图 15 密封腔内不同等半径面上的封严效率云图和流线图（i=60°）

Figure 15. Sealing efficiency contours and streamlines at different iso-radius surfaces in wheel-space （i=60°）

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图 16 孔出口高度距静盘1.5 mm位置的封严效率沿周向的分布

Figure 16. Circumferential distribution of sealing efficiency at location of 1.5 mm from static disc at radius of hole

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图 17 密封腔内距静盘1.5 mm截面上的封严效率云图和流线图（i=60°）

Figure 17. Sealing efficiency contours and streamlines at plane 1.5 mm from static disc in wheel-space （i=60°）

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图 18 密封腔内封严效率沿径向的分布

Figure 18. Radial distribution of sealing efficiency in wheel-space

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表 1 计算工况的边界条件

Table 1. Boundary condition of computation cases

参数	数值
主流进口总压/kPa	160
主流进口总温/K	328.15
封严气流量/（kg/s）	0.0172
次流进口静温/K	298.15
转速/（r/min）	3000
主流出口静压/Pa	101325
封严气流量分配比例	1∶1, 2∶1, 3∶1

下载: 导出CSV

表 2 网格无关性验证

Table 2. Grid-independent verification

参数	网格
参数	稀疏	中等	加密
主流域网格数量/10⁶	0.65	1.2	1.94
供气孔和盘腔域网格数量/10⁶	1.51	3.63	5.74
总网格数量/10⁶	2.16	4.83	7.68
封严效率	0.663	0.618	0.615

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