Performance Analysis of Solid Fuel Ramjet with Central Bluff Body

被引：0
|
作者：
Zhang N. [1 ]
Shi J.-G. [1 ]
Wang Z.-Y. [1 ]
Ma Y.-X. [2 ]
机构：
[1] School of Energy and Power Engineering, Nanjing University of Science and Technology, Nanjing
[2] Beijing Power Machinery Institute, Beijing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2022年 / 43卷 / 08期
关键词：
Burning surface regression rate; Combustion efficiency; Solid fuel ramjet; Thrust; Vortex combustion;
D O I：
10.13675/j.cnki.tjjs.210159
中图分类号：
学科分类号：
摘要：
In order to improve the combustion characteristics and working performance of the solid fuel ramjet，a solid fuel ramjet with a central bluff body is proposed. Based on the Renault transition and Eddy-Dissipation equations，the turbulent combustion model is established，and the internal flow field of the ramjet，as well as the regression rate，thrust and total pressure loss，were numerically analyzed. The results show that the internal flow process of the ramjet with a central bluff body is more complex. There are four vortices at the rear of the bluff body，which enhances the mixing of air and gas in the engine. The high-speed airflow in the blunt body pores and the small-scale vortices on both sides ensure the stability of the blunt body wake. Compared with the typical ramjet，adding a central bluff body in the combustion chamber could increase the area of high temperature zone in the SFRJ chamber and improve the temperature in the afterburner，which can increase the average burning surface regression rate of propellant by 26.1%，the thrust of engine by 22.1% and the combustion efficiency by 8.9%. © 2022 Journal of Propulsion Technology. All rights reserved.
引用
收藏
相关论文
共 27 条
  • [1] Mcdonald B，, Rice J., Solid Fuel Ramjet Fuel Optimization for Maximum Impulse-Density with Respect to Air to Fuel Ratio and Relative Fuel Regression Rates Derived from Thermogravimetric Analysis［J］, Aerospace Science and Technology, 86, 5, pp. 478-486, (2019)
  • [2] Zhang S, Zhang W., Numerical Investigation on the Regression Rate of Hybrid Rocket Motor with Star Swirl Fuel Grain［J］, Acta Astronautica, 127, 10, pp. 384-393, (2016)
  • [3] Whitmore S A, Walker S D., Engineering Model for Hybrid Fuel Regression Rate Amplification Using Helical Ports［J］, Journal of Propulsion and Power, 32, 2, pp. 1-10, (2016)
  • [4] Tian H，, Guo Y，, Wang P., Combustion Characteristics of Hybrid Rocket Motor with Segmented Grain［J］, Aerospace Science and Technology, 46, 10, pp. 537-547, (2015)
  • [5] Li W, Et al., Combustion Characteristics of Paraffin-Polyethylene Blends Fuel for Solid Fuel Ramjet ［J］, Journal of Aerospace Engineering, 33, 4, pp. 1-13, (2020)
  • [6] Yogeshkumar V，, Rathi N，, Ramakrishna P A., Solid Fuel Rich Propellant Development for Use in a Ramjet to Propel an Artillery Shell［J］, Defence Science Journal, 70, 3, pp. 329-335, (2020)
  • [7] Si-di Huang, Sungwook Hong, Et al., Enhancing Combustion Performance of Nano-Al/PVDF Composites with β -PVDF［J］, Combustion and Flame, 219, 9, pp. 467-477, (2020)
  • [8] Hashim S A，, Karmakar S，, Roy A., Effects of Ti and Mg Particles on Combustion Characteristics of Boron-HTPB-Based Solid Fuels for Hybrid Gas Generator in Ducted Rocket Applications［J］, Acta Astronautica, 160, 7, pp. 125-137, (2019)
  • [9] Rhode D，, Lilley D，, McLaughlin D., On the Prediction of Swirling Flow Fields Found in Axisymmetric Combustor Geometries［J］, Journal of Fluids Engineering, 104, 3, pp. 378-384, (1982)
  • [10] Lilley Samples D J，, Rhode D., Prediction of Swirling Reacting Flow in Ramjet Combustors［C］, Colorado：17th Joint Propulsion Conference, (1981)
123