高焓风洞液氧酒精空气燃烧加热器设计与试验  

Design and Test of Liquid Oxygen Alcohol Air Combustion Heater in High Enthalpy Wind Tunnel

作　　者：麻军德[1] 张洪春 于广雷 MA Jun-de;ZHANG Hong-chun;YU Guang-lei(Xi’an Aerospace Propulsion Test Technique Institute,Xi’an 710100,China)

机构地区：[1]西安航天动力试验技术研究所,陕西西安710100

出　　处：《推进技术》2023年第8期210-218,共9页Journal of Propulsion Technology

摘　　要：高焓风洞是进行吸气式发动机地面模拟试验的重要设施,为满足高温、高压来流模拟的需求,研制了一种基于液氧酒精燃烧的空气加热器。该加热器采用液液自击喷注与空气直流分区组织燃烧,并利用等离子体点火器实现中心点火,生成高焓来流。10kg/s量级燃烧加热器点火调试表明:该装置点火启动迅速,建压平稳并在点火器关闭后维持了稳定来流的生成,覆盖范围宽,在地面试验领域具有良好的应用前景。High enthalpy wind tunnel is an important facility for ground simulation test of air-breathing engine.In order to meet the demand of high temperature and high pressure flow simulation,an air heater based on liquid oxygen alcohol combustion was developed.The heater uses liquid-liquid self-impinging injection and airdirect current zone combustion,and uses plasma igniter to realize central ignition and generate high enthalpy to flow.The ignition debugging of the 10kg/s combustion heater shows that the device has a fast start-up,stable build-up pressure and maintains steady flow after the igniter is closed.The range is wide,and has a potential application prospect in ground testing field.

关 键 词：高焓风洞 空气液氧酒精三组元 燃烧加热 试验 加热器 

分 类 号：V416.8[航空宇航科学与技术—航空宇航推进理论与工程]