摘要
动量比是针栓喷注器的无量纲设计参数,对喷注器的混合效果及燃烧特性影响显著。为研究局部动量比变化对径向槽式气氧/煤油针栓喷注器燃烧特性的影响规律,使用数值仿真方法开展研究。仿真使用中心推进剂的偏转角模型作为煤油液滴的初始喷射角,并采用包含详细化学反应机理的火焰面模型对针栓喷注器燃烧场进行详细仿真,在此基础上研究局部动量比对燃烧场及燃烧效率的影响规律。结果表明:燃烧室内存在中心回流区和燃烧室头部回流区;局部动量比约为1时燃烧效率达到最高;燃烧室内温度场沿燃烧室轴向呈带状分布,沿燃烧室周向呈高低相间的齿轮状分布;随着局部动量比从0.53变化到1.46,燃烧模式呈现单火焰到双火焰再回到单火焰变化。
The momentum ratio is a dimensionless design parameter of pintle injector,which has a significant impact on the mixing effect and combustion characteristics of the injector.To investigate the influence of local momentum ratio changes on the combustion characteristics of a radial slot type gas oxygen/kerosene pintle injector,the numerical simulation method was used.The simulation used the deflection angle model of the central propellant as the initial injection angle of the kerosene droplet,and used flamelet model containing detailed chemical reaction mechanisms to simulate the combustion field of the pintle injector in detail.Based on this,the influence of local momentum ratio on the combustion field and combustion efficiency was studied.The results indicate that there are central recirculation zones and combustion chamber head recirculation zones in the combustion chamber.When the local momentum ratio is about 1,the combustion efficiency reaches its highest.The temperature field in the combustion chamber is distributed in a strip shape along the axial direction of the combustion chamber,and in a gear shape with alternating high and low directions along the circumferential direction of the combustion chamber.As the local momentum ratio changes from 0.53 to 1.46,the combustion mode changes from single flame to double flame and then back to single flame.
作者
徐天罡
杨宝娥
杨岸龙
张波涛
XU Tiangang;YANG Baoe;YANG Anlong;ZHANG Botao(National Key Laboratory of Aerospace Liquid Propulsion,Xi'an 710100,China;Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)
出处
《火箭推进》
北大核心
2025年第1期128-136,共9页
Journal of Rocket Propulsion
基金
国家重点基础研究发展计划(613193)。
关键词
针栓喷注器
局部动量比
回流区
燃烧效率
燃烧模式
pintle injector
local momentum ratio
recirculation zone
combustion efficiency
combustion mode
作者简介
徐天罡(1997-),男,硕士,工程师,研究领域为液体火箭发动机喷雾与燃烧技术。
