Influence of indirect initiation on the thermal efficiency of pulsed detonation engine

QIU Hua; WANG Wei; XIONG Cha

doi:10.13224/j.cnki.jasp.2016.08.009

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Influence of indirect initiation on the thermal efficiency of pulsed detonation engine

更新时间：2026-07-07

- Influence of indirect initiation on the thermal efficiency of pulsed detonation engine
- Vol. 31, Issue 8, Pages: 1860-1865(2016)
- 作者机构：
  
  1. 西北工业大学动力与能源学院,西安,710072
  2. 中国华能集团西安热工研究院有限公司,西安,710032
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2016.08.009
  CLC：
- Published：2016
- 稿件说明：
移动端阅览
邱华, 王玮, 熊姹. 间接起爆对脉冲爆震发动机热效率影响[J]. 航空动力学报, 2016, 31(8): 1860-1865.

doi: 10.13224/j.cnki.jasp.2016.08.009
邱华, 王玮, 熊姹. 间接起爆对脉冲爆震发动机热效率影响[J]. 航空动力学报, 2016, 31(8): 1860-1865. DOI： 10.13224/j.cnki.jasp.2016.08.009.

doi: 10.13224/j.cnki.jasp.2016.08.009 DOI：

摘要

建立了基于整个燃烧室内经历不同燃烧方式下所有工质来评估脉冲爆发动机平均循环热效率的方法，通过二维数值方法对两种采用不同数目障碍物的爆震管模型的起爆特性及循环热效率进行了研究，并分析了燃烧波传播的距离与DDT距离之比（定义为ξ）对模型热效率的影响.结果表明：①间接起爆方式及不同DDT强化装置都会影响系统的循环热效率；②就计算模型，当ξ接近1时，其系统平均循环热效率仅为理想爆震循环热效率的60%左右；③随着ξ的增加，间接起爆方式的影响迅速减弱；④当ξ为1.5时，系统平均循环热效率可达爆震燃烧热效率的93%.

Abstract

To analyze the influence of indirect initiation

a method was first established to evaluate the average cycle thermal efficiency of the system whose working fluid experienced different combustion processes in combustion chamber. Then

the thermal efficiency and deflagration to detonation transition (DDT) characteristics of two detonation tube models with different obstacles were investigated by the 2-D numerical simulations. The ratio of combustion wave run-up distance to DDT distance (defined as ξ) was also studied. The results show that: (1) the thermal efficiency of the pulsed detonation engine (PDE) model can be both influenced by the indirect initiation and different obstacles; (2) when ξ approaches to 1

the average thermal efficiency of the system is only 60% of ideal detonation cycle; (3) the effects of indirect initiation are weakened with the increase of ξ; (4) when ξ approaches to 1.5

the average thermal efficiency will reach 93% of ideal detonation cycle.

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Related Author

WANG Wei

QIU Hua

FAN Wei

XIONG Cha

QIN Ya-xin

YU Jun-li

GAO Ge

ZHENG Dian-feng

Related Institution

School of Power and Energy, Northwestern Polytechnical Univercity

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

College of Engineering, Peking University

College of Aerospace, Tsinghua University

College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics

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