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
计量
- 文章访问数: 116
- HTML浏览量: 39
- PDF量: 58
- 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

下载: 全尺寸图片幻灯片

图 2 余弦分布和线性分布的对比

Figure 2. Comparison of cosine and linear distributions

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

图 8 子午面静压云图对比

Figure 8. Comparison of static pressure contour at meridional plane

下载: 全尺寸图片幻灯片

图 9 进口总温分布

Figure 9. Total temperature distribution at inlet

下载: 全尺寸图片幻灯片

图 10 进口总压分布

Figure 10. Total pressure distribution at inlet

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 全尺寸图片幻灯片

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

下载: 导出CSV

参考文献(28)

[1]	MAZZAWY R S. Multiple segment parallel compressor model for circumferential flow distortion[J]. Journal of Engineering for Power,1977,99(2): 288-296. doi: 10.1115/1.3446288
[2]	STENNING A H. Inlet distortion effects in axial compressors[J]. Journal of Fluids Engineering,1980,102(1): 7-13. doi: 10.1115/1.3240630
[3]	屠宝锋,胡骏. 旋转总压畸变对压气机稳定性影响的三维非定常模型[J]. 航空动力学报,2011,26(2): 255-261. TU Baofeng,HU Jun. Three-dimensional unsteady model of effects of rotating inlet distortion on flow instability in compressor[J]. Journal of Aerospace Power,2011,26(2): 255-261. (in Chinese TU Baofeng, HU Jun. Three-dimensional unsteady model of effects of rotating inlet distortion on flow instability in compressor[J]. Journal of Aerospace Power, 2011, 26(2): 255-261. (in Chinese)
[4]	孙鹏,高海洋,都昆,等. 两种形式总压畸变对超声速压气机流场影响的数值研究[J]. 工程热物理学报,2013,34(5): 830-835. SUN Peng,GAO Haiyang,DU Kun,et al. Numerical study of a supersonic compressor with two forms of inlet total pressure distortion[J]. Journal of Engineering Thermophysics,2013,34(5): 830-835. (in Chinese SUN Peng, GAO Haiyang, DU Kun, et al. Numerical study of a supersonic compressor with two forms of inlet total pressure distortion[J]. Journal of Engineering Thermophysics, 2013, 34(5): 830-835. (in Chinese)
[5]	LI Qiushi,LYU Yongzhao,PAN Tianyu,et al. Development of a coupled supersonic inlet-fan Navier-Stokes simulation method[J]. Chinese Journal of Aeronautics,2018,31(2): 237-246. doi: 10.1016/j.cja.2017.11.011
[6]	GUO Jin,HU Jun,TU Baofeng,et al. A mixed-fidelity computational model of aero engine for inlet distortion[J]. Proceedings of the Institution of Mechanical Engineers,Part G: Journal of Aerospace Engineering,2019,233(14): 5295-5309.
[7]	MARBLE F E. Three-dimensional flow in turbomachines,aerodynamics of turbines and compressors[M]. Princeton,US: Princeton University Press,1964.
[8]	XU L,HYNES T P,DENTON J D. Towards long length scale unsteady modelling in turbomachines[J]. Proceedings of the Institution of Mechanical Engineers: Part A Journal of Power and Energy,2003,217(1): 75-82. doi: 10.1243/095765003321148718
[9]	CHIMA R V. A three-dimensional unsteady CFD model of compressor stability[R]. ASME GT-2006-90040,2006.
[10]	安玉戈,刘火星. 压气机进气畸变数值模拟技术研究[J]. 航空学报,2012,33(9): 1624-1632. AN Yuge,LIU Huoxing. Numerical simulation of compressor with inlet distortion[J]. Acta Aeronautica et Astronautica Sinica,2012,33(9): 1624-1632. (in Chinese AN Yuge, LIU Huoxing. Numerical simulation of compressor with inlet distortion[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(9): 1624-1632. (in Chinese)
[11]	尹超,胡骏,郭晋,等. 进气畸变对压气机性能影响的三维彻体力模型[J]. 航空动力学报,2015,30(9): 2241-2250. YIN Chao,HU Jun,GUO Jin,et al. Three-dimensional body-force model for effect on compressor performance of inlet distortion[J]. Journal of Aerospace Power,2015,30(9): 2241-2250. (in Chinese YIN Chao, HU Jun, GUO Jin, et al. Three-dimensional body-force model for effect on compressor performance of inlet distortion[J]. Journal of Aerospace Power, 2015, 30(9): 2241-2250. (in Chinese)
[12]	KIWADA G. Development of a body force description for compressor stability assessment[D]. Cambridge,US: Massachusetts Institute of Technology,2008.
[13]	Gong Y. A computational model for rotating stall and inlet distortions in multi-stage compressors[D]. Cambridge,US: Massachusetts Institute of Technology,1998.
[14]	HALL D K,GREITZER E M,TAN C S. Analysis of fan stage conceptual design attributes for boundary layer ingestion[J]. Journal of Turbomachinery,2017,139(7): 071012. doi: 10.1115/1.4035631
[15]	PETERS A,SPAKOVSZKY Z S,LORD W K,et al. Ultrashort nacelles for low fan pressure ratio propulsors[J]. Journal of Turbomachinery,2015,137(2): 021001. doi: 10.1115/1.4028235
[16]	HILL D J. Compressor performance scaling in the presence of non-uniform flow[D]. Ontatio,Canada: University of Windsor,2017.
[17]	LATOUR M T. Body force modeling of axial turbomachinery for analysis and design optimization[D]. Delft,Netherlands: Delft University of Technology,2020.
[18]	PICCOLI A. A body force method implementation in a computational fluid dynamics solver[D]. Padua,Italy: University of Padua,2020.
[19]	周游天,李军,彭生红,等. 插板进气畸变与压气机的耦合数值模拟[J]. 航空动力学报,2017,32(3): 568-576. ZHOU Youtian,LI Jun,PENG Shenghong,et al. Numerical simulation of flat baffle inlet distortion coupled with compressor[J]. Journal of Aerospace Power,2017,32(3): 568-576. (in Chinese ZHOU Youtian, LI Jun, PENG Shenghong, et al. Numerical simulation of flat baffle inlet distortion coupled with compressor[J]. Journal of Aerospace Power, 2017, 32(3): 568-576. (in Chinese)
[20]	THOLLET W. Body force modeling of fan-airframe interactions[D]. Toulouse,France: University of Toulouse,2017.
[21]	KUNKEL C,WERNER J,FRANKE D,et al. Introduction and commissioning of the new Darmstadt transonic compressor test facility[R]. ASME 2019-91165,2019.
[22]	徐诸霖,达兴亚,范召林,等. 一种适用于进气道/风扇一体化计算的体积力模型[J]. 推进技术,2019,40(4): 732-740. XU Zhulin,DA Xingya,FAN Zhaolin,et al. A body force model for the computation of inlet and fan integration[J]. Journal of Propulsion Technology,2019,40(4): 732-740. (in Chinese XU Zhulin, DA Xingya, FAN Zhaolin, et al. A body force model for the computation of inlet and fan integration[J]. Journal of Propulsion Technology, 2019, 40(4): 732-740. (in Chinese)
[23]	杨晨. 燃气轮机整机通流模型及其模拟技术研究[D]. 西安: 西北工业大学,2020. YANG Chen. Research on throughflow model and simulation methodology for full gas turbine engines[D]. Xi’an: Northwestern Polytechnical University,2020. (in Chinese YANG Chen. Research on throughflow model and simulation methodology for full gas turbine engines[D]. Xi’an: Northwestern Polytechnical University, 2020. (in Chinese)
[24]	时培杰,乔渭阳,魏佐君,等. 畸变进气下压气机三维黏性数值计算模型[J]. 航空动力学报,2012,27(7): 1472-1478. SHI Peijie,QIAO Weiyang,WEI Zuojun,et al. Investigation of three-dimensional viscous model for compressor with distortion inlet[J]. Journal of Aerospace Power,2012,27(7): 1472-1478. (in Chinese SHI Peijie, QIAO Weiyang, WEI Zuojun, et al. Investigation of three-dimensional viscous model for compressor with distortion inlet[J]. Journal of Aerospace Power, 2012, 27(7): 1472-1478. (in Chinese)
[25]	GREITZER E M,TAN C S,GRAF M B. Internal flow: concepts and applications[M]. Cambridge: Cambridge University Press,2007.
[26]	HE Xiao,ZHU Mingmin,XIA Kailong,et al. Validation and verification of RANS solvers for TUDa-GLR-OpenStage transonic axial compressor[J]. Journal of the Global Power and Propulsion Society,2023,7: 13-29. doi: 10.33737/jgpps/158034
[27]	郭晋,胡骏,尹超,等. 单级跨声速压气机进气畸变数值模拟[J]. 航空动力学报,2016,31(3): 669-677. GUO Jin,HU Jun,YIN Chao,et al. Numerical simulation of single-stage transonic compressor with inlet distortion[J]. Journal of Aerospace Power,2016,31(3): 669-677. (in Chinese GUO Jin, HU Jun, YIN Chao, et al. Numerical simulation of single-stage transonic compressor with inlet distortion[J]. Journal of Aerospace Power, 2016, 31(3): 669-677. (in Chinese)
[28]	FIDALGO V J,HALL C A,COLIN Y. A study of fan-distortion interaction within the NASA rotor 67 transonic stage[J]. Journal of Turbomachinery,2012,134(5): 051011. doi: 10.1115/1.4003850