二/三维稳定性模型失速预测能力对比研究

秦宇奇; 薛飞; 王庆勇; 覃海起; 王掩刚

doi:10.13224/j.cnki.jasp.20240309

二/三维稳定性模型失速预测能力对比研究

doi: 10.13224/j.cnki.jasp.20240309

西北工业大学动力与能源学院，西安 710129

基金项目: 国家自然科学基金（52276039）

详细信息

作者简介:
秦宇奇（2001-），男，硕士生，主要从事压气机稳定性研究

通讯作者:
王掩刚（1976-），男，教授，博士，主要从事叶轮机械设计与仿真研究。E-mail：wyg704@nwpu.edu.cn

中图分类号: V211
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出版历程
- 收稿日期: 2024-05-15
- 网络出版日期: 2025-11-27

Comparative study on the stall prediction ability of two/three-dimensional stability models

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
准确预测压气机失稳边界从而保证其结构完整性是国内外压气机设计者所面临的重大问题，本文以NASA Rotor 35转子以及双排轴流对转压气机为研究对象，首先评估了二维模型对单排及多排转子失速起始点的预估能力。结果显示：对于NASA Rotor 35转子，二维模型得到的失速点流量与实验结果之间的相对误差为1.87%；对于双排对转压气机，该模型与数值计算结果相差5.9%。针对二维模型在对转压气机失速预测精度低的问题，以体积力模型为基础，同时引入失速团传播速度预测模型，构建了三维失速预测模型。结果表明：所发展的三维模型预测得到的Rotor 35失速流量与实验值之间的相对误差为1.97%，对转压气机失速流量与数值计算结果之间的相对误差缩小至2.14%，极大解决了当前模型由于采用大量几何与流场简化方法而导致的预估能力不足的缺陷。
- 稳定性模型 /
- 失速预测 /
- 失速起始 /
- 对转压气机 /
- 跨声速转子
Abstract:
Accurately predicting compressor instability boundaries to ensure their structural integrity is a major problem faced by compressor designers at home and abroad, taking NASA Rotor 35 rotors and double-row axial flow counter-rotating compressors as the research objects, firstly, the ability of the two-dimensional model to predict the starting point of single-row and multi-row rotors is evaluated. The results show that for the NASA Rotor 35 rotor, the relative error between the stall point flow obtained by the two-dimensional model and the experimental results is 1.87%. For the double-row counter-rotating compressor, the model differed from the Computational Fluid Dynamics results by 5.9%. In order to solve the problem of low accuracy of the two-dimensional model in predicting the stall speed of the rotary compressor, a three-dimensional stall prediction model was constructed based on the volume force model and the prediction model of the propagation velocity of the stall group. The results show that the relative error between the stall flow rate of Rotor 35 predicted by the developed 3D model and the experimental value is 1.97%, and the relative error between the stall flow rate of the rotary compressor and the Computational Fluid Dynamics result is reduced to 2.14%, greatly solves the defect of insufficient estimation ability caused by the use of a large number of geometric and flow field simplification methods in the current model.
- stability model /
- stall prediction /
- stall point /
- counter-rotating compressor /
- transonic rotor

HTML

图 1 Rotor 35网格示意图

Figure 1. Schematic diagram of the Rotor 35 grid

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图 2 对转压气机网格示意图

Figure 2. Schematic diagram of the grid of the rotary compressor

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图 3 Rotor 35网格无关性验证

Figure 3. Rotor 35 grid independence verification

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图 4 对转压气机网格无关性验证

Figure 4. Verification of grid independence of the rotary compressor

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图 5 小扰动稳定性模型建立流程图

Figure 5. Flowchart for the establishment of the stability model of small perturbations

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图 6 Rotor 35特性图

Figure 6. Characteristic diagram of the Rotor 35

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图 7 Rotor 35出口相对气流角正切值及损失系数与进口相对气流角正切值的变化关系图

Figure 7. Diagram of the relationship between the tangent of the relative airflow angle of the outlet and the loss coefficient of the Rotor 35 and the tangent of the relative airflow angle of the inlet

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图 8 Rotor 35阻尼因子与质量流量的变化关系图

Figure 8. Diagram of Rotor 35 damping factor vs. mass flow

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图 9 对转压气机近失速工况99%叶高相对总压系数云图

Figure 9. Contour diagram of the relative total pressure coefficient of the 99% leaf height of the near-stall condition of the rotary compressor

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图 10 对转压气机出口相对气流角正切值及损失系数与进口相对气流角正切值的变化关系图

Figure 10. Diagram of the change between the tangent of the relative airflow angle of the outlet and the loss coefficient of the rotary compressor and the tangent of the relative airflow angle of the inlet

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图 11 对转压气机阻尼因子与质量流量的变化关系图

Figure 11. Diagram of the change between the damping factor and the mass flow rate of the counter-rotating compressor

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图 12 子午面径向速度与主流速度百分比图

Figure 12. Percentage of radial velocity to mainstream velocity of meridian surface

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图 13 三维数值模型建立流程图

Figure 13. 3D numerical model to establish a flow chart

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图 14 1stopt三维拟合Rotor 35中弧面效果示意图

Figure 14. Schematic diagram of the cambered surface effect of 1stopt 3D fitting Rotor 35

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图 15 ω取值点示意图

Figure 15. Schematic diagram of the value point of ω

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图 16 NASA Rotor 35离散网格图

Figure 16. Discrete grid diagram of NASA Rotor 35

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图 17 稳定性边界预测结果图

Figure 17. Stability boundary prediction result plot

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图 18 对转压气机离散网格图

Figure 18. Discrete grid diagram of the rotary compressor

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图 19 对转压气机失稳边界预测结果图

Figure 19. Prediction result of the instability boundary of the rotary compressor

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表 1 扰动波速度预测模型的验证

Table 1. Verification of disturbance wave velocity prediction model

$ \phi $	$ \gamma $	N	n	实验	计算	相对误差/%
0.35	50	1	1	19	15	21
			6	31	22	29
			12	66	24	64
0.35	50	3	1	32	28	13
			4	40	34	15
			12	60	36	40
0.55	35	1	1	15	13	5
		2	1	22	22	0
		3	1	26	26	6
		4	1	31	29	9
1.00	20	1	1	11	11	0
		2	1	20	20	4
		3	1	24	24	0
		4	1	28	28	13

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