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[1]王永佳,严宇,焦中天,等.脉冲爆震发动机非稳态排气及喷管设计分析[J].火箭推进,2021,47(06):93-100.
　WANG Yongjia,YAN Yu,JIAO Zhongtian,et al.Analysis on unsteady exhaust process of pulse detonation engine and design method of nozzle[J].Journal of Rocket Propulsion,2021,47(06):93-100.

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脉冲爆震发动机非稳态排气及喷管设计分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 47 期数: 2021年06期页码: 93-100 栏目: 专刊出版日期: 2021-12-31

Title:: Analysis on unsteady exhaust process of pulse detonation engine and design method of nozzle

文章编号:: 1672-9374(2021)06-0093-08

作者:: 王永佳¹; 严宇¹; 焦中天¹; 2; 张扬³; 范玮²; (1.西安航天动力研究液体火箭发动机技术重点实验室,陕西西安7101002.西北工业大学动力与能源学院,陕西西安7100723.西安现代控制技术研究所,陕西西安710054)

Author(s):: WANG Yongjia¹; YAN Yu¹; JIAO Zhongtian¹; 2; ZHANG Yang³; FAN Wei²; (1. Science and Technology on Liquid Rocket Engine Laboratory,Xian Aerospace Propulsion Institute,Xian 710100,China 2. School of Power and Energy,Northwestern Polytechnical University,Xian 710072,China 3. Xian Institute of Modern Control Technology, Xian 710054,China)

关键词:: 非稳态排气固定型面喷管压力平台区推力系数

Keywords:: unsteady exhaust fixed nozzle pressure platform thrust coefficient

分类号:: V439

文献标志码:: A

摘要:: 为初步得出适用于脉冲爆震发动机的喷管设计准则,基于数值模拟和理论分析方法,对脉冲爆震燃烧非稳态排气过程及适用的喷管设计方法进行了分析。脉冲爆震燃烧的非稳态排气过程可分为4个阶段:爆震波传播阶段、压力速降阶段、压力平台阶段和低压排气阶段。以直管中的C₂H₄/O₂脉冲爆震燃烧为例,排气压力在90.6 p_∞～1.72 p_∞范围内变化,若采用非稳态喷管设计方法,则可调喷管的扩张比对应为13～1。若采用固定型面喷管,则应当尽可能避免过膨胀状态下的激波损失,喷管设计点参数可使用排气压力平台区燃气参数进行计算,推力系数可达到95%左右。固定型面喷管设计点的气体参数对应最后一道泰勒膨胀波传播至出口时的燃气状态参数,可用经典爆震理论公式推导求解,从而实现脉冲爆震燃烧室固定型面喷管的快速设计。

Abstract:: In order to initially derive the nozzle design guidelines for pulse detonation engine,the unsteady exhaust process of pulse detonation combustion and the applicable nozzle design methods were analyzed based on numerical simulation and theoretical analysis methods. The unsteady exhaust process of pulse detonation combustion can be divided into four stages:detonation wave propagation stage,pressure downhill stage,pressure plateau stage and low pressure exhaust stage. Take the pulse detonation combustion of C₂H₄/O₂ in straight tube as an example,the expansion ratio of suitable adjustable nozzle changes from 13 to 1 corresponding to the exhaust pressure range from 90.6 p_∞to 1.72 p_∞. For the fixed nozzle scheme,the loss of shock wave triggered by over-expansion should be avoided. The design point of the fixed nozzle can be calculated by making use of the parameters of pressure platform,under which the thrust coefficient up to 0.95. The gas parameters of design point corresponding to the gas state when final Taylor expansion wave travels to the exit,which can be deduced from classical detonation theoretical equation,so as to realize the rapid design of fixed nozzle for the detonation.

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备注/Memo

收稿日期:2021-02-20 修回日期:2021-03-11
基金项目:国家自然科学基金(51176158 91441201 51376151) 教育部博士点基金(20126102110029) 西北工业大学博士论文创新基金(CX201504)
作者简介:王永佳(1991—),男,博士,高级工程师,研究领域为液体火箭发动机、爆震发动机和雾化燃烧。

更新日期/Last Update: 1900-01-01