Optimization method of turbulent flamelet model in afterburner

被引：0
|
作者：
Li A. [1 ]
Liu Y. [1 ]
Zhang X. [1 ]
机构：
[1] Aero-engine Thermal Environment and Structure Key Laboratory, Ministry of Industry and Information Technology, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2023年 / 38卷 / 05期
关键词：
afterburner; flamelet database; reynolds averaged navier-stokes (RANS) simulation; turbulent flamelet model; unsteady chemical kinetics;
D O I：
10.13224/j.cnki.jasp.20210303
中图分类号：
学科分类号：
摘要：
In the afterburner with high flow rate high, low pressure, oxygen poverty, the direct fuel injection is predominent, and the combustion model usually overestimates the reaction rate of the afterburner. Table-searching method is used in flamelet models with the advantage of fast calculation, but it is difficult to adjust the reaction rate. Based on the steady laminar flamelet model, unsteady chemical kinetic factors were added to adjust the reaction rate. Based on the experimental data, the key geometric parameters were established. The flamelet database was optimized, and the numerical simulation accuracy of this method was improved under high speed, low pressure, oxygen poverty and poor atomization effect. The results showed that the flamelet database formed by this optimization method can better simulate the complex chemical reaction process in afterburner. According to the calculation results, the simulation error of temperature distribution can be controlled within 15%, and the simulation error of average temperature can be controlled within 5%. © 2023 BUAA Press. All rights reserved.
引用
收藏
页码：1083 / 1089
页数：6
相关论文
共 18 条
  • [1] XIA Jiaohui, YANG Qian, WANG Huiru, Et al., Development analysis to afterburner combustion technology of turbofan, Aerospace Power, 4, pp. 17-21, (2020)
  • [2] ZHANG Zheng, Experiment study on fuel spray characteristics in model combustor, (2009)
  • [3] WANG Chengdong, Research on combustion characteristics of afterburner of small turbo-jet engine and validation of overall engine test, (2018)
  • [4] LU Bin, Investigation on mixing and combustion performances of lobe forced mixer for the afterburner, (2017)
  • [5] LIU Yuchen, Experimental study on spray characteristics of atomizing fan nozzle for afterburner, (2019)
  • [6] RAVICHANDRAN M，, SAMPATH S，, GANESAN V., Numerical analysis of two-ring flame stabilizer flows in aircraft afterburners, Numerical Heat Transfer: Part A Applications, 28, 1, pp. 85-101, (1995)
  • [7] ZHAO Jianxing, YAN Yingwen, Large-eddy simulation of turbulent reacting flows for the afterburner, Journal of Engineering Thermophysics, 25, pp. 237-239, (2004)
  • [8] SHAO Maomin, YAN Yingwen, LIU Yong, Et al., Parallel computing of flow field of a model afterburner, Journal of Aerospace Power, 21, 3, pp. 497-501, (2006)
  • [9] ZHANG Cheng, YE Taohong, CHEN Yiliang, Et al., Numerical simulation of two-phase turbulent combustion in a 3-D afterburner, Journal of Aerospace Power, 15, 4, pp. 397-400, (2000)
  • [10] ZHU Zuojin, ZHANG Xiaochun, Single phase combustion model and its application in a jet endine afterburner, Journal of Propulsion Technology, 18, 5, pp. 36-40, (1997)
12