Optimization and Parameter Analysis of Cavity in a Three-Dimensional Supersonic Combustor

被引：0
|
作者：
Zhu M.-J. [1 ]
Gu T.-L. [2 ]
Zhang S. [1 ]
Zheng Y. [1 ]
机构：
[1] School of Aeronautics and Astronautics, Zhejiang University, Hangzhou
[2] R&D Center, China Academy of Launch Vehicle Technology, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2018年 / 39卷 / 08期
关键词：
Cavity configuration; Optimization; Supersonic combustors; Surrogate models;
D O I：
10.13675/j.cnki.tjjs.2018.08.012
中图分类号：
学科分类号：
摘要：
The cavity has a great influence on the performance of supersonic combustors, such as combustion efficiency, drag characteristics and flame stability. The impact of the cavity parameter variation on the performance of combustors is complex coupled. A surrogate model based optimization and parameter analysis of the cavities in three-dimensional supersonic combustors with transverse fuel injection upstream were performed. The length, depth and sweepback angle of cavities were first designed by orthogonal experiment. Numerical simulations were applied to analyze the performance and flow fields of the test cases. Surrogate models of the combustion efficiency and total pressure recovery coefficient with the design variables were constructed. Based on the complex system optimization strategy, optimization of the cavity parameters were carried out twice to provide the Pareto front by the non-dominated sorting genetic algorithm (NSGA-Ⅱ). The results show that the optimal cavity configurations can be divided into narrow deep type, shallow long type and medium deep and long type, which correspond to rapid change section, gentle change section and extraordinary change section in the Pareto front. The combustion efficiency has a negative correlation with the length of cavities and a positive correlation with the depth of cavities. Whereas, the total pressure recovery coefficient has the opposite situations. Both combustion efficiency and total pressure recovery coefficient have few positive correlations with the sweepback angle. The combustors in the gentle change section have more uniform pressure distribution and higher total pressure recovery coefficient, which should be preferred when there is no need of high combustion efficiency. The length-to-depth ratio of the cavities in this section is about 2.67 to 8. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.
引用
收藏
页码：1780 / 1789
页数：9
相关论文
共 26 条
  • [1] Zang A., Tempel T., Yu K., Et al., Experimental Characterization of Cavity-Augmented Supersonic Mixing, 43rd AIAA Aerospace Sciences Meeting and Exhibit, (2005)
  • [2] Mathur T., Gruber M., Jackson K., Et al., Supersonic Combustion Experiments with a Cavity-Based Fuel Injector, Journal of Propulsion and Power, 17, 6, pp. 1305-1312, (2001)
  • [3] Ben-Yakar A., Hanson R.K., Cavity Flame-Holders for Ignition and Flame Stabilization in Scramjets: an Overview, Journal of Propulsion and Power, 17, 4, pp. 869-877, (2001)
  • [4] Gruber M., Baurle R., Mathur T., Et al., Fundamental Studies of Cavity-Based Flameholder Concepts for Supersonic Combustors, Journal of Propulsion and Power, 17, 1, pp. 146-153, (2001)
  • [5] Yu K.H., Wilson K.J., Schadow K.C., Effect of Flame-Holding Cavities on Supersonic-Combustion Performance, Journal of Propulsion and Power, 17, 6, pp. 1287-1295, (2001)
  • [6] Gruber M., Baurle R., Mathur T., Et al., Fundamental Studies of Cavity-Based Flameholder Concepts for Supersonic Combustors, Journal of Propulsion and Power, 17, 1, pp. 146-153, (2001)
  • [7] Kim K.M., Baek S.W., Han C.Y., Numerical Study on Supersonic Combustion with Cavity-Based Fuel Injection, International Journal of Heat and Mass Transfer, 47, 2, pp. 271-286, (2004)
  • [8] Geng H., Zhou J., Zhai Z.-C., Et al., Influence of Cavity Geometry on Flow and Combustion of Transverse Fuel Jets in a Supersonic Combustor, Journal of Propulsion Technology, 28, 6, pp. 599-606, (2007)
  • [9] Cai Z., Yang Y., Sun M., Et al., Experimental Investigation on Ignition Schemes of a Supersonic Combustor with the Rearwall-Expansion Cavity, Acta Astronautica, 123, pp. 181-187, (2016)
  • [10] Cai Z., Wang Z., Sun M., Et al., Effect of Combustor Geometry and Fuel Injection Scheme on the Combustion Process in a Supersonic Flow, Acta Astronautica, 129, pp. 44-51, (2016)
123