Key technology of digital twin system for aero-engine combustors
-
摘要:
通过曲线坐标系浸没边界方法（IBM），在设计阶段可以实现对真实航空发动机燃烧室的高保真虚实映射，保留全部几何结构信息。在IBM方法基础上，采用大涡模拟（LES）结合概率密度函数输运方程湍流燃烧模型（TPDF），对双旋流燃烧室、某单头部直流燃烧室以及某折流燃烧室1/10模型进行真实结构仿真，测试数字孪生体系关键技术的有效性。对比预测结果和实验结果，双旋流燃烧室的旋流器出口附近轴向、径向、切向速度平均误差分别为15.7%、23.8%、15.0%；非稳态解析了真实直流燃烧室与折流燃烧室的详细湍流燃烧场，出口温度分布的平均相对误差分别为11.66%和17.95%。因此基于虚实映射得到的燃烧室数字孪生体系具有一定的有效性，该方法具有潜在的工程应用前景。
-
关键词:
- 数字孪生 /
- 高保真建模 /
- 大涡模拟（LES） /
- 概率密度函数输运方程湍流燃烧模型（TPDF） /
- 浸没边界方法（IBM）
Abstract:The curvilinear coordinate system’s immersion boundary method (IBM) can be used to realize high-fidelity virtual-real mapping of the real aero-engine combustor in the design stage, and retain all the geometric structure information. Based on the IBM method, large eddy simulation (LES) combined with transported probability density functional turbulent combustion model (TPDF) was used to simulate the real structure of a double-swirler combustor, a single-head model of a throughflow combustor and 1/10 model of a slinger combustor, and test the effectiveness of key technologies of the digital twin system. Compared with the prediction and experiment results, the average errors of axial, radial and tangential velocities near the outlet of the swirler of the double-swirler combustor were 15.7%, 23.8% and 15.0%, respectively. The detailed turbulent combustion fields of the single-head model of a throughflow combustor and the slinger combustor were analyzed under the unsteady state, and the average relative errors of the outlet temperature distribution were 11.66% and 17.95%, respectively. Therefore, the combustor’s digital twin system obtained based on virtual real mapping has certain effectiveness, and the proposed method has potential engineering application prospects.
-
图 3 扫描线经边线穿入模型内示意图
Figure 3. Schematic diagram of scan line edge penetration into the model
图 4 采用贴体网格时粒子反弹示意图
Figure 4. Schematic diagram of the particles bounce with body-fitted grids
图 5 采用IBM时网格标记与真实壁面关系示意图
Figure 5. Schematic diagram of the relationship between the grid marker and the real wall with IBM
图 6 采用IBM时粒子与壁面碰撞后反弹示意图
Figure 6. Schematic diagram of particle bounce after collision with the wall when using IBM
图 7 粒子在单个时间步内穿越壁面示意图
Figure 7. Schematic of a particle crossing a wall in a single time step
图 8 粒子与薄壁碰撞后反弹示意图
Figure 8. Schematic diagram of particle bounce after collision with thin wall
图 10 计算采用的双旋流燃烧室几何模型与背景网格
Figure 10. Double-swirler combustor geometry model and grid used for calculation
图 11 三维流线图与中间截面时均轴向速度云图
Figure 11. Three-dimensional streamline plot and time-averaged axial velocity nephogram on the intermediate section
图 12 旋流器出口时均轴向速度分布
Figure 12. Time-averaged axial velocity distribution at the outlet of the swirler
图 13 旋流器出口时均切向速度分布
Figure 13. Time-averaged tangential velocity distribution at the outlet of the swirler
图 14 旋流器出口时均径向速度分布
Figure 14. Time-averaged radial velocity distribution at the outlet of the swirler
图 19 笛卡儿坐标系下并行块划分情况示意图与三维IBM网格标记
Figure 19. Schematic diagram of the parallel block division in the Cartesian coordinate system and IBM grid markers
图 20 曲线坐标系下单头部燃烧室并行块划分情况示意图与三维IBM网格标记
Figure 20. Schematic diagram of the parallel block division of single-head combustor in the curvilinear coordinate system and IBM grid markers
图 21 单头部燃烧室瞬态三维流线图
Figure 21. Transient three-dimensional streamline diagram of the single-head combustor
图 22 单头部燃烧室中央截面瞬态速度矢量图
Figure 22. Transient velocity vector nephogram on the central section of the single-head combustor
图 23 单头部燃烧室中央截面瞬态温度云图
Figure 23. Transient temperature nephogram on the central section of the single-head combustor
图 24 单头部燃烧室中央截面煤油质量分数云图
Figure 24. Kerosene mass fraction nephogram on the central section of the single-head combustor
图 25 单头部燃烧室中央截面时均温度云图
Figure 25. Time-average temperature nephogram on the central section of the single-head combustor
图 26 单头部燃烧室出口测点位置时均径向温度分布
Figure 26. Time-average radial temperature distribution of the single-head combustor exit measurement point
图 28 曲线坐标系下折流燃烧室并行块划分情况示意图
Figure 28. Schematic diagram of the parallel block division of slinger combustor in the curvilinear coordinate system
图 30 冷态时均流场三维流线图
Figure 30. Three-dimensional streamline diagram of cold time-averaged flow field
图 31 用于求解气相燃烧和液滴粒子轨迹的三维网格标记
Figure 31. Three-dimensional grid markers for solving gas phase combustion and droplet particle trajectories
图 32 冷态工况煤油液滴粒子运动轨迹
Figure 32. Trajectory of kerosene droplet particles in cold working condition
图 33 折流燃烧室中央截面瞬态温度云图
Figure 33. Central section transient temperature nephogram of slinger combustor
图 34 折流燃烧室中央截面瞬态气相煤油质量分数云图和氧气质量分数等值线图
Figure 34. Central section transient vapor phase kerosene mass fraction and oxygen mass fraction nephogram of slinger combustor
图 36 涡轮导向器叶片前部截面时均温度云图
Figure 36. Time-averaged temperature nephogram on the front section of the turbine guide blade
图 37 燃烧室出口测点位置时均径向温度分布
Figure 37. Time-average radial temperature distribution at the combustor exit measurement point
表 1 双旋流燃烧室算例时均速度平均相对误差
Table 1. Time-averaged velocity average relative error of the double-swirler combustor
高度/mm 速度方向 模拟误差/% AECSC-IBM FLUENT 2 轴向 13.8 15.1 5 轴向 12.0 11.4 10 轴向 21.2 15.8 2 切向 15.4 11.2 5 切向 11.6 11.2 10 切向 18.0 14.3 2 径向 36.6 34.5 5 径向 16.9 11.9 10 径向 18.0 10.2 
下载: 导出CSV
表 2 燃烧室出口测点位置温度模拟值与实验值相对误差
Table 2. Relative error between the simulation and experimental value of temperature distribution at the outlet of the combustion chamber
相对高度 温度/K 相对误差/% 实验[23] 模拟 0.1650 924.4 928.9 0.48 0.3325 959.7 929.5 3.14 0.5000 980.0 1039.7 6.09 0.6675 1049.6 1265.1 20.53 0.8350 799.5 1275.4 59.51
下载: 导出CSV
-
[1] 王方,王煜栋,姜胜利,等. AECSC-JASMIN湍流燃烧仿真软件研发和检验[J]. 航空学报,2021,42(12): 128-140.WANG Fang,WANG Yudong,JIANG Shengli,et al. Development and inspection of AECSC-JASMIN turbulent combustion simulation software[J]. Acta Aeronautica et Astronautica Sinica,2021,42(12): 128-140. (in Chinese) [2] JONES W P,TYLISZCZAK A. Large eddy simulation of spark ignition in a gas turbine combustor[J]. Flow, Turbulence and Combustion,2010,85(3): 711-734. [3] JONES W P,MARQUIS A J,VOGIATZAKI K. Large-eddy simulation of spray combustion in a gas turbine combustor[J]. Combustion and Flame,2014,161(1): 222-239. doi: 10.1016/j.combustflame.2013.07.016 [4] 曾家,金捷,张晟,等. 基于LES-PDF方法的双旋流模型燃烧室数值模拟[J]. 气体物理,2019,4(5): 52-64. doi: 10.19527/j.cnki.2096-1642.0789ZENG Jia,JIN Jie,ZHANG Sheng,et al. Numerical simulation of double-swirled model combustor based on LES-PDF[J]. Physics of Gases,2019,4(5): 52-64. (in Chinese) doi: 10.19527/j.cnki.2096-1642.0789 [5] TACHIBANA S,SAITO K,YAMAMOTO T,et al. Experimental and numerical investigation of thermo-acoustic instability in a liquid-fuel aero-engine combustor at elevated pressure: validity of large-eddy simulation of spray combustion[J]. Combustion and Flame,2015,162(6): 2621-2637. doi: 10.1016/j.combustflame.2015.03.014 [6] CHENG Y,JIN T,LUO K,et al. Large eddy simulations of spray combustion instability in an aero-engine combustor at elevated temperature and pressure[J]. Aerospace Science and Technology,2021,108: 106329.1-106329.16. [7] 阎超,于剑,徐晶磊,等. CFD模拟方法的发展成就与展望[J]. 力学进展,2011,41(5): 562-589. doi: 10.6052/1000-0992-2011-5-lxjzJ2010-082YAN Chao,YU Jian,XU Jinglei,et al. On the achievements and prospects for the method of computational fluid dynamics[J]. Advances in Mechanics,2011,41(5): 562-589. (in Chinese) doi: 10.6052/1000-0992-2011-5-lxjzJ2010-082 [8] PESKIN C S. Flow patterns around heart values: a numerical method[J]. Journal of Computational Physics,1972,10(2): 252-271. doi: 10.1016/0021-9991(72)90065-4 [9] MOHAMMADI M,NASSAB S A G. Application of the immersed boundary method in solution of radiative heat transfer problems[J]. Journal of Quantitative Spectroscopy and Radiative Transfer,2021,260(2): 107467.1-107467.16. [10] MITTAL R,IACCARINO G. Immersed boundary methods[J]. Annual Reviews of Fluid Mechanics,2005,37: 239-261. doi: 10.1146/annurev.fluid.37.061903.175743 [11] GROPP W, LUSK E, SKJELLUM A. Using MPI: portable parallel programming with the message-passing interface[M]. London: MIT Press, 2014. [12] 郭涛,张纹惠,王文全,等. 基于IBM法的低雷诺数下涡激振动高质量比效应的研究[J]. 工程力学,2022,39(3): 222-232. doi: 10.6052/j.issn.1000-4750.2021.07.0566GUO Tao,ZHANG Wenhui,WANG Wenquan,et al. Effects of heigh mass and dampling ratio on VIV of a circular cylinder with low reynolds number[J]. Engineering Mechanics,2022,39(3): 222-232. (in Chinese) doi: 10.6052/j.issn.1000-4750.2021.07.0566 [13] 张漫,王铮钧,王晶,等. 航空发动机内流全场流动的大涡模拟[J]. 航空动力,2021,19(2): 59-60.ZHANG Man,WANG Zhengjun,WANG Jing,et al. Large eddy simulation on internal flow of aero engine[J]. Aerospace Power,2021,19(2): 59-60. (in Chinese) [14] 金捷,刘邓欢. 航空发动机燃烧室湍流两相燃烧模型发展现状[J]. 南京航空航天大学学报,2016,48(3): 303-309. doi: 10.16356/j.1005-2615.2016.03.002JIN Jie,LIU Denghuan. Recent advance in turbulent two-phase combustion models[J]. Journal of Nanjing University of Aeronautics and Astronautics,2016,48(3): 303-309. (in Chinese) doi: 10.16356/j.1005-2615.2016.03.002 [15] JONES W P,PRASAD V N. Large eddy simulation of the sandia flame series (D–F) using the Eulerian stochastic field method[J]. Combustion and Flame,2010,157(9): 1621-1636. doi: 10.1016/j.combustflame.2010.05.010 [16] WANG F,LIU R,DOU L,et al. A dual timescale model for micromixing and its application in LES/TPDF simulations of turbulent nonpremixed flames[J]. Chinese Journal of Aerinautics,2019,32(4): 52-64. [17] JABERI F A,COLUCCI P J,JAMES S,et al. Filtered mass density function for large-eddy simulation of turbulent reacting flows[J]. Journal of Fluid Mechanics,1999,401(2): 85-121. [18] LAGAE A,DUTRE P. An efficient ray-quadrilateral intersection test[J]. Journal of Graphics Tools,2005,10(4): 23-32. doi: 10.1080/2151237X.2005.10129208 [19] 杨庆山,陈飞新,赵乐,等. 基于大涡模拟的大气边界层湍流强度对低矮房屋风荷载特性影响研究[J]. 工程力学,2021,38(12): 25-38. doi: 10.6052/j.issn.1000-4750.2020.10.0778YANG Qingshan,CHEN Feixin,ZHAO Le,et al. Effects on upstream turbulence intensity on aerodynamic loads of low-rise buildings in atmospheric boundary layer flow using large eddy simulation[J]. Engineering Mechanics,2021,38(12): 25-38. (in Chinese) doi: 10.6052/j.issn.1000-4750.2020.10.0778 [20] 闫渤文,马晨燕,赵乐,等. 强台风下带挑檐双坡低矮房屋风荷载特性大涡模拟方法适用性研究[J]. 工程力学,2021,38(11): 66-78, 133. doi: 10.6052/j.issn.1000-4750.2020.10.0738YAN Bowen,MA Chenyan,ZHAO Le,et al. Study in the applicability of large eddy simulation method for wind load characteristics of low-rise buildings with eaves and double slopes under strong typhoons[J]. Engineering Mechanics,2021,38(11): 66-78, 133. (in Chinese) doi: 10.6052/j.issn.1000-4750.2020.10.0738 [21] MEIER U,HEINZE J,FREITAG S,et al. Spray and flame structure of a generic injector at aeroengine conditions[J]. The Journal of Engineering for Gas Turbines and Power,2012,134(3): 031503.1-031503.9. [22] 刘邓欢,金捷,王方,等. 涡轮喷气式发动机整机环境下折流燃烧室性能实验[J]. 航空动力学报,2015,30(10): 2410-2415.LIU Denghuan,JIN Jie,WANG Fang,et al. Performance test of slinger combustor of turbojet engine running in engine test[J]. Journal of Aerospace Power,2015,30(10): 2410-2415. (in Chinese) [23] KUNDU K P, DEUR J. A simplified reaction mechanism for calculation of emissions in hydrocarbon (Jet-A) combustion[C]//29th Joint Propulsion Conference and Exhibit. Monterey, US: AIAA, 2012: 1993-2341. -
点击查看大图
计量
- 文章访问数: 1035
- HTML浏览量: 455
- PDF量: 215
- 被引次数: 0