涡喷发动机全三维流-热-固耦合建模方法

魏杰; 温孟阳; 杨合理; 王旭; 郑新前

doi:10.13224/j.cnki.jasp.20230232

涡喷发动机全三维流-热-固耦合建模方法

doi: 10.13224/j.cnki.jasp.20230232

魏杰^1,,
温孟阳²,
杨合理²,
王旭³,
郑新前^1,*, ,

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
3.
广西虹鹰动力科技有限公司，广西桂林 541003

基金项目: 国家科技重大专项（2017-Ⅱ-0004-0016，J2019-Ⅰ-0021-0020）

详细信息

作者简介:
魏杰（1994-），男，博士生，主要从事航空发动机转子叶尖间隙预测研究。E-mail：weij2018@mails.tsinghua.edu.cn

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
计量
- 文章访问数: 767
- HTML浏览量: 353
- PDF量: 151
- 被引次数: 0
出版历程
- 收稿日期: 2023-04-09
- 网络出版日期: 2024-06-18

Modeling of turbojet engines based on three-dimensional fluid-thermal-structural coupling method

WEI Jie^1
,,
WEN Mengyang²,
YANG Heli²,
WANG Xu³,
ZHENG Xinqian^{1,*
, ,}

1.
School of Vehicle and Mobility，Tsinghua University，Beijing 100084，China
2.
Institute for Aero Engine，Tsinghua University，Beijing 100084，China
3.
Guangxi Hawk Power Technology Company Limited，Guilin Guangxi 541003，China

摘要

摘要:
建立了单通道流-热和全通道热-固的耦合建模方法，对某涡喷发动机进行了全三维流-热-固耦合分析，并与不考虑耦合的方法进行了对比，在温度、应力和变形等方面均有较大差异。流-热耦合的压气机转子叶片温度较不耦合偏低15 K，三级扩压器温度较不耦合偏低10～20 K。热-固耦合的压气机转子最大等效应力比不耦合小31 MPa（4.7%），径向变形比不耦合大0.02 mm（11.1%）。流-热-固耦合预测的设计点涡轮叶尖间隙变化0.54 mm。该方法实现了整机温度场、应力场、变形场的分析，综合评估了部件的强度和变形，为部件优化提供了数据支撑。
- 涡喷发动机 /
- 全三维数值仿真 /
- 流-热-固耦合 /
- 间隙预测 /
- 结构分析
Abstract:
A single-passage fluid-thermal and full-passage thermo-structural coupling modeling method was established, and three-dimensional fluid-thermal-structural coupling analysis of a turbojet engine was carried out. Compared with the method without coupling, there were great differences in temperature, stress, and deformation. The temperature of the compressor impeller of the fluid-thermal coupling method was 15 K lower than that of the uncoupled, and the temperature of the three-stage diffuser was 10—20 K lower than that of the uncoupled. The maximum equivalent stress of the compressor impeller of the thermal-structural coupling method was 31 MPa (4.7%) smaller than that of the uncoupled, and the radial deformation of the compressor impeller was 0.02 mm (11.1%) larger than that of the uncoupled. The tip clearance variation of the turbine at the design point predicted by the fluid-thermal-structural coupling analysis was 0.54 mm. This method realized the analysis of the temperature field, stress field, and deformation field of the whole engine, comprehensively evaluated the strength and deformation of components, and provided data support for component optimization.
- turbojet engine /
- three-dimensional numerical simulation /
- fluid-thermal-structural coupling method /
- tip clearance prediction /
- structural analysis

HTML

图 1 某型涡喷发动机单通道计算域

Figure 1. Single-passage computational domain of a type of turbojet engine

下载: 全尺寸图片幻灯片

图 2 某型涡喷发动机试车台示意图

Figure 2. Schematic diagram of the turbojet engine test stand

下载: 全尺寸图片幻灯片

图 3 某型涡喷发动机推力试验验证

Figure 3. Test verification of the thrust for a type of turbojet engine

下载: 全尺寸图片幻灯片

图 4 发动机单通道固体几何

Figure 4. Single-passage solid geometry of the engine

下载: 全尺寸图片幻灯片

图 5 流-热耦合单通道计算域

Figure 5. Single-passage computational domain of the fluid-thermal coupling method

下载: 全尺寸图片幻灯片

图 6 主要部件计算网格

Figure 6. Computational mesh for the main components

下载: 全尺寸图片幻灯片

图 7 喷油量控制逻辑

Figure 7. Control logic of the fuel injection

下载: 全尺寸图片幻灯片

图 8 全通道固体计算域

Figure 8. Full-passage computational domain of the solid

下载: 全尺寸图片幻灯片

图 9 扩压器第2级和第3级接触连接

Figure 9. Contact connection between the second and third stage of the diffuser

下载: 全尺寸图片幻灯片

图 10 压气机盘与转轴接触连接

Figure 10. Contact connection between the compressor disk and the rotating shaft

下载: 全尺寸图片幻灯片

图 11 全通道热-固耦合计算流程

Figure 11. Full-passage computational process of the thermal-structural method

下载: 全尺寸图片幻灯片

图 12 整机流体温度场对比

Figure 12. Comparison of the fluid temperature for the engine

下载: 全尺寸图片幻灯片

图 13 压气机转子壁面温度场对比

Figure 13. Comparison of the wall temperature for the compressor impeller

下载: 全尺寸图片幻灯片

图 14 扩压器叶片壁面温度场对比

Figure 14. Comparison of the wall temperature for the diffuser

下载: 全尺寸图片幻灯片

图 15 燃烧室外流体域壁面温度场对比

Figure 15. Comparison of the wall temperature for the flow of the combustor

下载: 全尺寸图片幻灯片

图 16 整机结构单通道温度场

Figure 16. Temperature field of the single-passage for the engine structure

下载: 全尺寸图片幻灯片

图 17 整机应力分布

Figure 17. Stress distribution of the engine

下载: 全尺寸图片幻灯片

图 18 整机变形分布

Figure 18. Deformation distribution of the engine

下载: 全尺寸图片幻灯片

图 19 压气机盘应力分布

Figure 19. Deformation distribution of the compressor impeller

下载: 全尺寸图片幻灯片

图 20 涡轮盘应力分布

Figure 20. Deformation distribution of the turbine rotor

下载: 全尺寸图片幻灯片

图 21 压气机转子应力对比

Figure 21. Stress comparison of the compressor impeller

下载: 全尺寸图片幻灯片

图 22 压气机转子变形对比

Figure 22. Deformation comparison of the compressor impeller

下载: 全尺寸图片幻灯片

图 23 压气机转子温度分布

Figure 23. Temperature distribution of the compressor impeller

下载: 全尺寸图片幻灯片

图 24 涡轮转子叶尖间隙示意图

Figure 24. Schematic of the tip clearance of the turbine rotor

下载: 全尺寸图片幻灯片

表 1 发动机部件参数

Table 1. Components parameters of the engine

部件	周期数	材料
外机匣	18	Al7075
压气机转子	9	TC4
扩压器第1级	23	Al7075
扩压器第2级	79	Al7075
扩压器第3级	97	Al7075
燃烧室	18	GH4169
涡轮导向器	36	K4002
涡轮转子	53	K4002
尾喷管	6	310S
轴系结构	18	38CrMoAlA

下载: 导出CSV

表 2 接触类型

Table 2. Contact types

接触条件	接触类型	法向距离	切向滑移
绑定	线性	无间隙	无滑移
不分离	线性	无间隙	允许滑移
无摩擦	非线性	允许有间隙	允许滑移
粗糙	非线性	允许有间隙	无滑移
有摩擦	非线性	允许有间隙	允许滑移

下载: 导出CSV

参考文献(18)

[1]	江华栋. 微型涡轮发动机总体设计及全通流数值模拟研究[D]. 哈尔滨: 哈尔滨工业大学,2021. JIANG Huadong. Overall design and numerical thorough flow simulation of micro turbine engine[D]. Harbin: Harbin Institute of Technology,2021. (in Chinese JIANG Huadong. Overall design and numerical thorough flow simulation of micro turbine engine[D]. Harbin: Harbin Institute of Technology, 2021. (in Chinese)
[2]	王威. 某型涡喷发动机控制及仿真平台开发[D]. 南昌: 南昌大学,2022. WANG Wei. A turbojet engine control and simulation platform development[D]. Nanchang: Nanchang University,2022. (in Chinese WANG Wei. A turbojet engine control and simulation platform development[D]. Nanchang: Nanchang University, 2022. (in Chinese)
[3]	申涛. 微型涡喷发动机建模与控制的研究[D]. 南京: 南京航空航天大学,2012. SHEN Tao. Research on simulation and control system for micro turbine engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2012. (in Chinese SHEN Tao. Research on simulation and control system for micro turbine engine[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2012. (in Chinese)
[4]	陆瑶. 31X涡喷发动机建模与性能分析研究[D]. 长沙: 国防科学技术大学,2013. LU Yao. Modeling and performance research of the turbine engine[D]. Changsha: National University of Defense Technology,2013. (in Chinese LU Yao. Modeling and performance research of the turbine engine[D]. Changsha: National University of Defense Technology, 2013. (in Chinese)
[5]	陈敏泽,陈玉春,贾琳渊,等. 微型涡喷发动机总体综合设计应用研究[J]. 航空工程进展,2022,13(4): 107-116. CHEN Minze,CHEN Yuchun,JIA Linyuan,et al. Research on the application of integrated design on micro turbojet engine[J]. Advances in Aeronautical Science and Engineering,2022,13(4): 107-116. (in Chinese CHEN Minze, CHEN Yuchun, JIA Linyuan, et al. Research on the application of integrated design on micro turbojet engine[J]. Advances in Aeronautical Science and Engineering, 2022, 13(4): 107-116. (in Chinese)
[6]	杨合理. 多级轴流压气机流动机理及改进设计研究[D]. 北京: 清华大学,2016. YANG Heli. Flow mechanisms and improved design of multistage axial compressors[D]. Beijing: Tsinghua University,2016. (in Chinese YANG Heli. Flow mechanisms and improved design of multistage axial compressors[D]. Beijing: Tsinghua University, 2016. (in Chinese)
[7]	屠秋野,陈劼,蒋平,等. 压气机过渡段造型及三维数值模拟[J]. 航空动力学报,2015,30(6): 1414-1422. TU Qiuye,CHEN Jie,JIANG Ping,et al. Geometric modeling and 3-D numerical simulation for gooseneck of compressor[J]. Journal of Aerospace Power,2015,30(6): 1414-1422. (in Chinese TU Qiuye, CHEN Jie, JIANG Ping, et al. Geometric modeling and 3-D numerical simulation for gooseneck of compressor[J]. Journal of Aerospace Power, 2015, 30(6): 1414-1422. (in Chinese)
[8]	冀国锋,殷明霞,桂幸民. 某小型离心压气机气动设计[J]. 航空动力学报,2010,25(3): 557-564. JI Guofeng,YIN Mingxia,GUI Xingmin. Aerodynamic design of a small centrifugal compressor[J]. Journal of Aerospace Power,2010,25(3): 557-564. (in Chinese JI Guofeng, YIN Mingxia, GUI Xingmin. Aerodynamic design of a small centrifugal compressor[J]. Journal of Aerospace Power, 2010, 25(3): 557-564. (in Chinese)
[9]	张绍文,石建成,李维,等. 高负荷涡轮进口导向叶片叶型设计及验证[J]. 航空动力学报,2021,36(1): 185-192. ZHANG Shaowen,SHI Jiancheng,LI Wei,et al. Design and validation of high-lift turbine nozzle guide vane profile[J]. Journal of Aerospace Power,2021,36(1): 185-192. (in Chinese ZHANG Shaowen, SHI Jiancheng, LI Wei, et al. Design and validation of high-lift turbine nozzle guide vane profile[J]. Journal of Aerospace Power, 2021, 36(1): 185-192. (in Chinese)
[10]	曾军,王彬,卿雄杰. 某双级高压涡轮全三维计算[J]. 航空动力学报,2012,27(11): 2553-2561. ZENG Jun,WANG Bin,QING Xiongjie. Three-dimensional analysis of two-stage high pressure turbine[J]. Journal of Aerospace Power,2012,27(11): 2553-2561. (in Chinese ZENG Jun, WANG Bin, QING Xiongjie. Three-dimensional analysis of two-stage high pressure turbine[J]. Journal of Aerospace Power, 2012, 27(11): 2553-2561. (in Chinese)
[11]	PÉREZ ARROYO C,DOMBARD J,DUCHAINE F,et al. Towards the large-eddy simulation of a full engine: integration of a 360 azimuthal degrees fan,compressor and combustion chamber: Part Ⅰ methodology and initialization[J]. Journal of the Global Power and Propulsion Society,2021: 133115.
[12]	WANG F,CARNEVALE M,LU G,et al. Virtual gas turbine: pre-processing and numerical simulations: ASME Paper GT2016-56227[R]. Seoul,South Korea: ASME,2016.
[13]	AI Weiguo,FLETCHER T H. Computational analysis of conjugate heat transfer and particulate deposition on a high pressure turbine vane[J]. Journal of Turbomachinery,2012,134(4): 041020. doi: 10.1115/1.4003716
[14]	HUNT D,YUAN Y M,GARDNER I. Modelling conjugate heat transfer within a gas turbine secondary air system using 1D and 2-3D solid models in thermo-fluid system simulation: ASME Paper GT2021-59930[R]. Virtual, Online: ASME,2021.
[15]	LIU Longgang,GU Chunwei,REN Xiaodong. An investigation of the conjugate heat transfer in an intercooled compressor vane based on a discontinuous Galerkin method[J]. Applied Thermal Engineering,2017,114: 85-97. doi: 10.1016/j.applthermaleng.2016.11.190
[16]	ZHENG Xinqian,DING Chuang,ZHANG Yangjun. Influence of different loads on the stresses of multistage axial compressor rotors[J]. Proceedings of the Institution of Mechanical Engineers,Part G: Journal of Aerospace Engineering,2017,231(5): 787-798. doi: 10.1177/0954410016642461
[17]	ZHENG Xinqian,DING Chuang. Effect of temperature and pressure on stress of impeller in axial-centrifugal combined compressor[J]. Advances in Mechanical Engineering,2016,8(6): 1-11.
[18]	徐建新,许立敬. 基于流热固耦合的航空发动机涡轮叶片仿真分析[J]. 航空科学技术,2023,34(2): 26-33. XU Jianxin,XU Lijing. Simulation analysis on aero-engine turbine blades based on fluid-thermal-solid coupling[J]. Aeronautical Science & Technology,2023,34(2): 26-33. (in Chinese XU Jianxin, XU Lijing. Simulation analysis on aero-engine turbine blades based on fluid-thermal-solid coupling[J]. Aeronautical Science & Technology, 2023, 34(2): 26-33. (in Chinese)