摘要
为了突破冲压发动机地面试验系统关键组件空气加热器稳定燃烧的关键技术,提出了一种液氧/酒精/空气三组元高效稳定的组织燃烧技术,对该加热器技术方案进行了缩尺试验研究,并验证了不同的空气流量比例对加热器点火特性和燃烧特性的影响。试验表明,该加热器具有点火可靠、启动迅速、燃烧稳定和大范围变工况的工作能力以及燃烧效率最高达到0.98的燃烧特性。研究发现,当加热器的空气流量比例由40%增加到70%时,并没有对点火启动特性和燃烧稳定性产生不利的影响,但是引起燃烧效率下降了0.03。从侧面验证了在液体火箭发动机燃烧器中增加少量的空气可以提高燃烧稳定性和燃烧效率。
In order to master the key technology of stable combustion of the air heater which is a key unit of ramjet ground test system, a new technical scheme of tri-propellant（liquid oxygen/alcohol/air） air heater is proposed so as to realize high-efficiency stable combustion. The sub-scale test for the technical scheme of the air heater was researched. The effects of different air flow proportion on ignition characteristic and combustion performance of the heater were verified. The experimental results show that the heater has reliable ignition, quick start-up, steady burning and better working capacity of variable working condition in wide range, and its combustion efficiency is up to0.98. It is found in the test analysis that when the air flow proportion of heater increases from 40% to70%, there is no effect on the ignition characteristic and the combustion stability, but the combustion efficiency decreases by 0.03. On the other hand, it also proves that the increase of a small quantity of air to the combustor in liquid-propellant rocket engine can improve its combustion stability and efficiency.
出处
《火箭推进》
CAS
2016年第1期26-32,共7页
Journal of Rocket Propulsion
基金
国家863项目(2012AA702302)
关键词
三组元空气加热器
缩尺试验
燃烧效率
tri-propellant air heater
sub-scale test
combustion efficiency
