Two-dimensional numerical study for effects of MHD accelerator technology on thrust augmentation in pulse detonation engine

被引：0

作者：

Lin L. ^{[1
]}

Weng C.-S. ^{[1
]}

机构：

[1] National Key Laboratory Transient Physics, Nanjing University of Science and Technology, Nanjing

来源：

| 1600年 / Journal of Propulsion Technology卷 / 37期

关键词：

Flow field; Magnetohydrodynamics; Pulse detonation engine; Thrust;

D O I：

10.13675/j.cnki.tjjs.2016.05.025

中图分类号：

学科分类号：

摘要：

The gas-liquid two-phase detonation model with magnetohydrodynamic was established to study how the MHD accelerator technology affects the augmentation in pulse detonation engine. The ignition, detonation and exhaust process of pulse detonation engine with MHD accelerator were calculated using the CE/SE method. The flow field of pulse detonation engine with MHD accelerator was simulated. The mechanism of thrust augmentation of MHD accelerator was revealed. The effects of MHD accelerator on pulse detonation engine's propulsion performance under different magnetic flux density and length conditions were analyzed. Calculation results show that the MHD accelerator can be applied to the thrust compensation of pulse detonation engine. With the increase of magnetic flux density and acceleration section length, pulse detonation engine's average thrust increases remarkably. When the MHD acceleration section length is 0.4 m and magnetic flux density is 2T, the average thrust increases by 30.457%, and the thrust increasing rate reaches the maximum. © 2016, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：985 / 991

页数：6

共 11 条

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