基于体积力模型的跨声压气机进气畸变数值模拟

邱佳慧; 杨晨; 赵红亮; 张敏; 杜娟; 聂超群

doi:10.13224/j.cnki.jasp.20220526

基于体积力模型的跨声压气机进气畸变数值模拟

doi: 10.13224/j.cnki.jasp.20220526

邱佳慧^{1, 2, 3, 4},
杨晨^{1, 2, 3, 4,*, ,},
赵红亮⁵,
张敏^{1, 2, 3, 4},
杜娟^{1, 2, 3, 4},
聂超群^{1, 2, 3, 4}

1.
中国科学院工程热物理研究所先进燃气轮机实验室，北京 100190
2.
中国科学院先进能源动力重点实验室，北京 100190
3.
中国科学院轻型动力创新研究院，北京 100190
4.
中国科学院大学工程科学学院，北京 100049
5.
华北电力大学能源动力与机械工程学院，北京 102206

基金项目: 国家自然科学基金（51922098，51790510）；国家重大科技专项（2017-Ⅱ-0004-0017）

详细信息

作者简介:
邱佳慧（1996-），女，博士生，主要从事叶轮机械气动热力学研究

通讯作者:
杨晨（1993-），男，博士，主要从事叶轮机械气动热力学研究。E-mail：yangchen@iet.cn

中图分类号: V231.3
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- 文章访问数: 38
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- 被引次数: 0
出版历程
- 收稿日期: 2022-07-21
- 网络出版日期: 2023-12-29

Numerical simulation of transonic compressor with inlet distortion based on body-force model

QIU Jiahui^{1, 2, 3, 4},
YANG Chen^{1, 2, 3, 4,*
, ,},
ZHAO Hongliang⁵,
ZHANG Min^{1, 2, 3, 4},
DU Juan^{1, 2, 3, 4},
NIE Chaoqun^{1, 2, 3, 4}

1.
Advanced Gas Turbine Laboratory，Institute of Engineering Thermo-physics，Chinese Academy of Sciences，Beijing 100190，China
2.
Key Laboratory of Advanced Energy and Power，Chinese Academy of Sciences，Beijing 100190，China
3.
Innovation Academy for Light-Duty Gas Turbine，Chinese Academy of Sciences，Beijing 100190，China
4.
School of Engineering Science，University of Chinese Academy of Sciences，Beijing 100049，China
5.
School of Energy，Power and Mechanical Engineering，North China Electric Power University，Beijing 102206，China

摘要

摘要:
为快速评估进气畸变对压气机气动性能的影响，发展了一种基于体积力模型的进气畸变三维数值模拟方法。首先研究了体积力源项的建模理论和方法，并将该模型嵌入商业软件CFX中对Darmstadt单级跨声压气机在均匀进气条件下进行了计算及验证。进一步利用该方法对压气机在180°总温、总压畸变条件下的特性及流场进行了数值模拟，结果表明：该方法能再现进气畸变对压气机特性的影响，同时压气机内部畸变流场强三维特征与URANS（全环非定常）结果基本保持一致；在总温和总压畸变条件下，压气机与上游畸变流场的耦合作用趋势相反。相比URANS计算，该方法对计算资源的消耗能降低5个数量级，并能有效捕捉畸变流场在压气机内部的传递特征。
- 压气机 /
- 进气畸变 /
- 快速评估 /
- 体积力模型 /
- 耦合作用 /
- 气动性能
Abstract:
In order to numerically study the impact of distorted inflow on a transonic compressor with less computational costs, a three-dimensional simulation method was developed based on body-force model (BFM). Firstly, the modeling method of building body-force source term was studied. The test data of the Darmstadt transonic compressor were used to verify the body-force model in performance prediction of the blade rows with clean inflow. Furthermore, steady simulations with a 180° circumferential total temperature and total pressure distortion were performed using BFM. This showed that the BFM can reproduce the distorted compressor characteristics. The evolution of the inlet distortion through the compressor and the circumferential phase change of the total temperature across the rotor were in line with unsteady Reynolds averaged Navier-Stockes (URANS). Under inlet total temperature and pressure distortion, the coupling trend of compressor and upstream distorted flow field was opposite. Compared with URANS, the BFM can significantly reduce the computational costs by 5 orders of magnitude while effectively capturing the main flow features inside the compressor.
- compressor /
- inlet distortion /
- rapid assessment /
- body-force model /
- coupling effect /
- aerodynamic performance

HTML

图 1 计算域网格

Figure 1. Computational domain and grid distribution

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图 2 余弦分布和线性分布的对比

Figure 2. Comparison of cosine and linear distributions

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图 3 不同分布形式下熵云图的对比

Figure 3. Comparison of entropy contour with different distribution forms

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图 4 转子前缘探测面周向各扇区示意图

Figure 4. Schematic of circumferential sector before rotor leading edge

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图 5 Darmstadt 跨声压气机均匀进气特性曲线

Figure 5. Performance map of Darmstadt compressor with clean inlet

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图 6 不同轴向位置气流参数沿径向分布的对比

Figure 6. Comparison of flow parameters spanwise distributions at different axial locations

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图 7 子午面绝对切向速度云图对比

Figure 7. Comparison of absolute tangential velocity contour at meridional plane

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图 8 子午面静压云图对比

Figure 8. Comparison of static pressure contour at meridional plane

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图 9 进口总温分布

Figure 9. Total temperature distribution at inlet

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图 10 进口总压分布

Figure 10. Total pressure distribution at inlet

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图 11 压气机不同进气畸变特性点位置

Figure 11. Position of characteristic point with different inlet distortion of compressor

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图 12 总温畸变下转子出口总温云图对比

Figure 12. Comparison of total temperature contour at rotor outlet with total temperature distortion

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图 13 总温畸变下三维体积力计算结果

Figure 13. Calculation results of three-dimensional body-force model with total temperature distortion

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图 14 总温畸变下压气机上游流场密流及静压的周向分布

Figure 14. Distributions of mass flux and static pressure ahead of rotor with total temperature distortion

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图 15 总温畸变下转子前缘绝对切向速度云图

Figure 15. Contour of absolute tangential velocity before rotor leading edge with total temperature distortion

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图 16 总压畸变下压气机上游流场密流及静压的周向分布

Figure 16. Distributions of mass flux and static pressure ahead of rotor with total pressure distortion

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图 17 总压畸变下转子前缘截面绝对切向速度云图

Figure 17. Contour of absolute tangential velocity before rotor leading edge with total pressure distortion

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表 1 压气机基本参数

Table 1. Basic parameters of compressor

参数数值

功率/kW 800
扭矩/（N·m） 350
最大转速/（r/min） 21000
转子最大直径/m 0.38
轮毂比～0.5
转子叶尖相对马赫数～1.4

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