Experimental investigations of deflagration to detonation transition in toroidal section tube

YU Jun-li; QIN Ya-xin; GAO Ge

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Experimental investigations of deflagration to detonation transition in toroidal section tube

更新时间：2026-07-07

- Experimental investigations of deflagration to detonation transition in toroidal section tube
- Vol. 25, Issue 8, (2010)
- 作者机构：
  
  北京航空航天大学能源与动力工程学院, 航空发动机气动热力科技重点实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2010
- 稿件说明：
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YU Jun-li, QIN Ya-xin, GAO Ge. Experimental investigations of deflagration to detonation transition in toroidal section tube[J]. 2010, 25(8).
DOI：

YU Jun-li, QIN Ya-xin, GAO Ge. Experimental investigations of deflagration to detonation transition in toroidal section tube[J]. 2010, 25(8). DOI：

摘要

为了实现在环截面爆震管封闭端同时点火

采用了先在预燃室中点火

再通过八路支管将火焰引入到爆震管封闭端

各个支管长度一样

因此可看成在环管封闭端多点同时点火.实验结果显示

在爆震管封闭端火焰汇聚形成激波点火

可在环管封闭端附近直接产生爆震波.在爆震管中安放扰流片时

流动阻力使爆震速度偏低

无扰流片时

爆震速度接近理论值.不加扰流片当量比在1.0左右

火焰速度会出现爆燃或爆震两种随机状态

当量比到1.1时可避免这种状况.

Abstract

In order to implement ignition at the same time at closed end of toroidal detonation tube

a way of ignition at a point and several branches of the same length was used.The results show that detonation wave can be formed immediately through shock produced by converging flame at the closed end of tube.With obstacles

the velocity of detonation will be decreased due to flow drag.Without obstacles

the velocity of detonation is close to the theory value.At about equivalence ratio 1.0

the flame velocity without obstacles may generate deflagration or detonation at random.And this random state can be avoided at equivalence ratio 1.1.

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Related Author

YU Jun-li

QIN Ya-xin

GAO Ge

WANG Wei

QIU Hua

FAN Wei

XIONG Cha

YANG Xi-qiong

Related Institution

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics

School of Power and Energy, Northwestern Polytechnical Univercity

School of Power and Energy,Northwestern Polytechnical University

Gas Turbine Technology Department, Xi'an Thermal Power Research Institute Company Limited

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics

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