氢喷前温度递降对液氧/气氢燃烧特性的影响  

Influence of Hydrogen Injection Temperature on LOX/GH_(2) Combustion Characteristics

作　　者：王珏[1] 丁兆波[2] Wang Jue;Ding Zhao-bo(China Academy of Launch Vehicle Technology,Beijing,100076;Beijing Aerospace Propulsion Institute,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2021年第5期44-49,共6页Missiles and Space Vehicles

摘　　要：为了研究氢喷前温度对液氧/气氢同轴直流式喷嘴燃烧特性的影响,分别通过单喷嘴热试验和缩比喷注器热试验两种途径,对氢氧发动机推力室用大流量喷嘴进行了氢喷前温度递降试验。其中单喷嘴热试验中氢喷前温度范围90~230 K,在温度递降过程中未发生不稳定燃烧。缩比喷注器热试验中氢喷前温度范围65~145 K,在温度递降到70 K时激发了不稳定燃烧。研究表明:液氧/气氢同轴直流式喷嘴燃烧存在一个稳定工作氢温的下限,如果在低于该下限的温度下工作,则将激励燃烧不稳定性。所选用的大流量喷嘴具有一定的燃烧稳定性裕度,氢喷前温度递降试验可以作为氢氧发动机燃烧稳定性评定的一套可行方法。To investigate the effects of hydrogen injection temperature on combustion efficiency and stability,the hydrogen temperature ramping tests for LOX/LH2 rocket engine thrust chamber injector are performed through single element injector and sub-scale combustor hot fire tests.The hydrogen injection temperature conditions of single element injector tests are about 90~230 K,and there is no combustion instability during the temperature ramping.The hydrogen injection temperature conditions of sub-scale combustor tests are about 65~145 K,and combustion instability is initiated at a hydrogen injection temperature of 70 K.The test results demonstrated that a stability boundary for a specific combustor configuration may be established by varying the hydrogen injection temperature.Hydrogen injection temperature ramping is a valid and reliable technique for rating the relative combustion stability of LOX/LH2 rocket engine.

关 键 词：氢喷射温度 燃烧特性 单喷嘴 缩比喷注器 热试验 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]