基于三维体积力模型的离心压气机喘振预测方法

曾翰轩; 范腾博; 温孟阳; 魏杰; 王钧莹; 孙振中; 郑新前

doi:10.13224/j.cnki.jasp.20220047

基于三维体积力模型的离心压气机喘振预测方法

doi: 10.13224/j.cnki.jasp.20220047

曾翰轩¹,
范腾博¹,
温孟阳²,
魏杰¹,
王钧莹¹,
孙振中²,
郑新前^{1, 2,*, ,}

1.
清华大学车辆与运载学院，北京 100084
2.
清华大学航空发动机研究院，北京 100084

基金项目: 国家科技重大专项（2017-Ⅱ-0004-0016，J2019-Ⅰ-0011）

详细信息

作者简介:
曾翰轩（1994-），男，博士生，主要从事航空发动机气动稳定性研究

通讯作者:
郑新前（1977-），男，教授、博士生导师，博士，主要从事航空发动机气动热力学研究。E-mail：zhengxq@tsinghua.edu.cn

中图分类号: V231
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- 被引次数: 0
出版历程
- 收稿日期: 2022-01-25
- 网络出版日期: 2023-10-16

Surge prediction of radial compressors based on three-dimensional body-force method

1.
School of Vehicle and Mobility，Tsinghua University，Beijing 100084，China
2.
Institute for Aero Engine，Tsinghua University，Beijing 100084，China

摘要

摘要:
为了实现对喘振流动现象的准确、快速预测，提出了一种基于三维体积力模型的离心压气机喘振预测方法，并在一款跨声速离心压气机上进行了应用，对以叶轮进口叶尖“回流泡”、喘振中的旋转失速，以及蜗壳诱发的非对称流动为代表的典型喘振流场结构进行了捕捉。通过与经试验校核的全三维非定常雷诺平均Navier-Stokes（URANS）方法进行对比表明：本文提出的离心压气机喘振预测方法，针对主要喘振流动特征的预测具备与全三维URANS方法相当的能力，同时计算时间约为全三维URANS方法的1/20。
- 离心压气机 /
- 喘振 /
- 体积力模型 /
- 模拟方法 /
- 非定常雷诺平均Navier-Stokes方法
Abstract:
To predict the three-dimensional and unsteady flow features of surge accurately and efficiently, a method of surge simulation for centrifugal compressors based on the three-dimensional body-force model was proposed. The method was further validated on a transonic centrifugal compressor. Typical flow field features like the development of the recirculation bubble at the impeller inlet tip, the existence of rotating stall during surge, and volute-induced asymmetry were captured. By comparing against the unsteady Reynolds averaged Navier-Stokes (URANS) results (validated by the experimental results), it can be shown that the proposed method is capable of predicting key features of surge, with the calculation time about 1/20 of the URANS method.
- centrifugal compressor /
- surge /
- body-force model /
- modeling method /
- unsteady Reynolds averaged Navier-Stokes method

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图 1 后弯叶轮出口的滑移效应

Figure 1. Slip effect at the outlet of a back-sweep impeller

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图 2 压缩系统示意图

Figure 2. Sketch of the compression system

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图 3 试验压气机实物图^[16]

Figure 3. Tested compressor geometry^[16]

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图 4 体积力模型计算域及计算网格

Figure 4. Computational domain and mesh for the BDF model

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图 5 URANS模型计算域及计算网格

Figure 5. Computational domain and mesh for the UNRANS model

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图 6 网格无关性验证

Figure 6. Mesh independence validation

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图 7 BDF模型与URANS模型预测喘振特性对比

Figure 7. Comparison of the predicted surge characteristics between BDF model and URANS model

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图 8 喘振过程中压气机各截面静压变化对比

Figure 8. Comparison of the static pressure at several compressor stations during surge

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图 9 流动崩溃阶段压气机瞬时轴向速度云图（对应时刻见图7）

Figure 9. Compressor axial velocity contour during the flow reversal （corresponding time is shown in Fig.7）

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图 10 喘振过程中压气机瞬时马赫数云图（50%扩压器叶高截面，对应时刻见图7）

Figure 10. Mach number contour during surge （50% diffuser blade span, corresponding time is shown in Fig.7）

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图 11 失速团的周向迁移（P1和P2位置见图10）

Figure 11. Circumferential migration of the stall cell （the locations of P1 and P2 are shown in Fig.10）

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图 12 重新增压阶段压气机瞬时马赫数云图（50%扩压器叶高截面，对应时刻见图8）

Figure 12. Mach number contour during the repressurization stage （50% diffuser blade span, corresponding time is shown in Fig.8）

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表 1 压气机无量纲参数

Table 1. Compressor design parameters

参数	符号	数值
叶轮周期数	$ {Z_{\text{i}}} $	16
进口轮毂比	$ R $	0.63
扩压器周期数	$ {Z_{\text{d}}} $	16
扩压器进口半径比	${r_3}/{r_2}$	1.18
扩压器出口半径比	${r_4}/{r_2}$	1.44
叶轮叶尖马赫数	$ M{a_{\text{u}}} $	1.4
流量系数	$ \phi $	0.04
压升系数	$ \psi $	0.47
比转速	$ {N_{\text{s}}} $	0.70
B参数	$ B $	1.22

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表 2 URANS模型网格参数

Table 2. Mesh specifications for URANS model

参数	数值
参数	网格1	网格2
进口段流向膨胀比	1.05	1.05
叶轮径向网格层数	50	63
叶轮流向网格层数	100	120
叶轮周向网格层数（单通道）	16	16
叶轮间隙网格层数	17	21
扩压器径向网格层数	50	63
扩压器流向网格层数	50	64
扩压器周向网格层数（单通道）	35	48
总网格数/万	746	1539

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表 3 BDF网格参数

Table 3. Mesh specifications for BDF model

参数	数值
参数	网格1	网格2
径向网格层数	15	21
周向网格层数	100	140
进口段流向网格层数	50	70
叶轮流向网格层数	30	40
连接段流向网格层数	8	10
扩压器流向网格层数	23	30
总网格数/万	22	52

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参考文献(18)

[1]	赵阳,王志恒,席光. 离心压缩机喘振动态特性的数值研究[J]. 工程热物理学报,2019,40(10): 2252-2258. ZHAO Yang,WANG Zhiheng,XI Guang. Numerical investigation of dynamic characteristic of surge in a centrifugal compressor[J]. Journal of Engineering Thermophysics,2019,40(10): 2252-2258. (in Chinese)
[2]	郭强,竺晓程,杜朝辉,等. 带气腔的离心压缩机旋转失速的三维数值模拟[J]. 航空动力学报,2007,22(7): 1167-1172. doi: 10.13224/j.cnki.jasp.2007.07.024 GUO Qiang,ZHU Xiaocheng,DU Zhaohui,et al. Three-dimensional numerical simulation of rotating stall inside a centrifugal compressor with plenum model[J]. Journal of Aerospace Power,2007,22(7): 1167-1172. (in Chinese) doi: 10.13224/j.cnki.jasp.2007.07.024
[3]	YAMADA K, FURUKAWA M, ARAI H, et al. Evolution of reverse flow in a transonic centrifugal compressor at near-surge[R]. ASME GT2017-63568, 2017.
[4]	SHAHIN I,GADALA M,ALQARADAWI M,et al. Large eddy simulation for a deep surge cycle in a high-speed centrifugal compressor with vaned diffuser[J]. Journal of Turbomachinery,2015,137(10): 101007. doi: 10.1115/1.4030790
[5]	TREBINJAC I,BENICHOU E,BUFFAZ N. Full-annulus simulation of the surge inception in a transonic centrifugal compressor[J]. Journal of Thermal Science,2015,24(5): 442-451. doi: 10.1007/s11630-015-0807-x
[6]	GONG Y,TAN C S,GORDON K A,et al. A computational model for short-wavelength stall inception and development in multistage compressors[J]. Journal of Turbomachinery,1999,121(4): 726-734. doi: 10.1115/1.2836726
[7]	CHIMA R V. A three-dimensional unsteady CFD model of compressor stability[R]. ASME GT2006-90040, 2006.
[8]	郑宁,邹正平,徐力平. 风扇进气畸变三维非定常数值模拟技术研究[J]. 航空动力学报,2007,22(1): 60-65. doi: 10.3969/j.issn.1000-8055.2007.01.011 ZHENG Ning,ZOU Zhengping,XU Liping. 3-D unsteady numerical simulation of fan/compressor with inlet distortion[J]. Journal of Aerospace Power,2007,22(1): 60-65. (in Chinese) doi: 10.3969/j.issn.1000-8055.2007.01.011
[9]	ZENG Hanxuan,ZHENG Xinqian,VAHDATI M. A method of stall and surge prediction in axial compressors based on three-dimensional body-force model[J]. Journal of Engineering for Gas Turbines and Power,2022,144(3): 031021. doi: 10.1115/1.4053103
[10]	QIU X W, MALLIKARACHCHI C, ANDERSON M. A new slip factor model for axial and radial impellers[R]. ASME GT2007-27064, 2007.
[11]	GREITZER E M. Surge and rotating stall in axial flow compressors: Part Ⅰ theoretical compression system model[J]. Journal of Engineering for Power,1976,98(2): 190-198. doi: 10.1115/1.3446138
[12]	GREITZER E M. Surge and rotating stall in axial flow compressors: Part Ⅱ experimental results and comparison with theory[J]. Journal of Engineering for Power,1976,98(2): 199-211. doi: 10.1115/1.3446139
[13]	HUANG Qiangqiang,ZHANG Meijie,ZHENG Xinqian. Compressor surge based on a 1D-3D coupled method: Part 1 method establishment[J]. Aerospace Science and Technology,2019,90: 342-356. doi: 10.1016/j.ast.2019.04.040
[14]	DUMAS M, VO H D, YU H. Post-surge load prediction for multi-stage compressors via CFD simulations[R]. ASME GT2015-42748, 2015.
[15]	LIN Yun,FAN Tengbo,ZHENG Xinqian. Roles of recirculating bubble on the performance of centrifugal compressors[J]. Aerospace Science and Technology,2021,118: 107073. doi: 10.1016/j.ast.2021.107073
[16]	ZHENG Xinqian,SUN Zhenzhong,KAWAKUBO T,et al. Experimental investigation of surge and stall in a turbocharger centrifugal compressor with a vaned diffuser[J]. Experimental Thermal and Fluid Science,2017,82: 493-506. doi: 10.1016/j.expthermflusci.2016.11.036
[17]	MORENO J,DODDS J,SHEAF C,et al. Aerodynamic loading considerations of three-shaft engine compression system during surge[J]. Journal of Turbomachinery,2021,143(12): 121002. doi: 10.1115/1.4051207
[18]	EVERITT J N,SPAKOVSZKY Z S. An investigation of stall inception in centrifugal compressor vaned diffuser1[J]. Journal of Turbomachinery,2013,135(1): 011025. doi: 10.1115/1.4006533