Influences of H2O mass fraction and chemical kinetics mechanism on the turbulent diffusion combustion of H2-O2 in supersonic flows
- 作者：Wei Huang ; gladrain2001@yahoo.com.cn ; Zhen-guo Wang ; Shi-bin Li ; Wei-dong Liu
- 关键词：Aerospace propulsion system ; Chemical kinetics mechanism ; Vitiation effect ; Hydrogen combustion ; Supersonic flow ; Turbulent diffusion combustion
- 刊名：Acta Astronautica
- 出版年：2012
- 期刊代码：1_00945765
- 类别：et
- 出版时间：July-August, 2012
- 卷：76
- 期：Complete
- 页码：51-59
- 文件大小：570 K
摘要
Hydrogen is one of the most promising fuels for the airbreathing hypersonic propulsion system, and it attracts an increasing attention of the researchers worldwide. In this study, a typical hydrogen-fueled supersonic combustor was investigated numerically, and the predicted results were compared with the available experimental data in the open literature. Two different chemical reaction mechanisms were employed to evaluate their effects on the combustion of H2-O2, namely the two-step and the seven-step mechanisms, and the vitiation effect was analyzed by varying the H2O mass fraction. The obtained results show that the predicted mole fraction profiles for different components show very good agreement with the available experimental data under the supersonic mixing and combustion conditions, and the chemical reaction mechanism has only a slight impact on the overall performance of the turbulent diffusion combustion. The simple mechanism of H2-O2 can be employed to evaluate the performance of the combustor in order to reduce the computational cost. The H2O flow vitiation makes a great difference to the combustion of H2-O2, and there is an optimal H2O mass fraction existing to enhance the intensity of the turbulent combustion. In the range considered in this paper, its optimal value is 0.15. The initiated location of the reaction appears far away from the bottom wall with the increase of the H2O mass fraction, and the H2O flow vitiation quickens the transition from subsonic to supersonic mode at the exit of the combustor.