Experimental Study on Effects of Initial Fuel Temperature on Performance for Two-Phase Detonation

被引：0

作者：

Wang Y.-J. ^{[1
]}

Yan Y. ^{[1
]}

Zhang Y. ^{[2
]}

Fan W. ^{[3
]}

Zhang Q.-B. ^{[3
]}

Jiao Z.-T. ^{[1
,3
]}

机构：

[1] Science and Technology on Liquid Rocket Engine Laboratory, Xi'an Aerospace Propulsion Institute, Xi'an

[2] Xi'an Institute of Modern Control Technology, Xi'an

[3] School of Power and Energy, Northwestern Polytechnical University, Xi'an

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2021年 / 42卷 / 04期

关键词：

Distance of deflagration to detonation transition; Initial temperature of fuel; Mach disk; Total pressure of exhaust gas; Wave velocity;

D O I：

10.13675/j.cnki.tjjs.200630

中图分类号：

学科分类号：

摘要：

To investigate the effects of initial fuel temperature on the performance of two-phase detonation, experiments under different fuel temperature conditions from 30℃ to 200℃ were conducted in a 24mm detonation tube at 10Hz, utilizing kerosene and oxygen as fuel and oxidant, respectively. The results show that, with the rise of the initial temperature of fuel, the steady propagation velocity of the flame front increases gradually, the combustion stability increases, the two-phase detonation peak pressure increases, the detonation initiation distance reduces. In addition, the observation of detonation tail flame at different initial fuel temperatures shows that, with the increase of fuel temperature, both the total pressure of unsteady exhaust process and the thrust available for the engine increase. © 2021, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：892 / 897

页数：5

共 17 条

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