航空发动机燃烧室出口温度分布调试与测试技术研究  

Debugging and Testing Technology for Temperature Distribution of Aero Engine Outlet

作　　者：赵然[1] 蔡文哲[2,3] Zhao Ran;Cai Wenzhe(Naval Military Representative Office in the Third Research Academy,CASIC,Beijing 100074,China;Beijing Power Machinery Institute,Beijing 100074,China;Beihang University,Beijing 100191,China)

机构地区：[1]海军驻航天三院军事代表室,北京100074 [2]北京动力机械研究所,北京100074 [3]北京航空航天大学,北京100191

出　　处：《战术导弹技术》2018年第5期84-89,共6页Tactical Missile Technology

摘　　要：针对航空发动机燃烧室出口温度场品质控制问题,从相应的调试机理出发,开展了燃烧室雾化机构,火焰筒进气规律,火焰筒型面规律三类调试手段的综述研究。研究中采用了热电偶测量、激光测量、声学测量三种温度测量手段。通过改变雾化机构安装数量/安装位置等能够起到改善温度场的效果;火焰筒进气规律对出口温度场的影响主要是对掺混孔的开孔规律/旋流器结构进行调整,且掺混孔面积增大一般有利于改善温度场;改变型面规律对尺寸较小的折流燃烧室和回流燃烧室温度场能够起到显著的调试效果。According to the two phase flow and chemical reaction kinetic model for hydro-carbon fuel combustion, the debug method for outlet temperature distribution of combustion can be included for three categories. These three categories are atomizing mechanism, distribution law of air flow in combustor and the structure shape of the combustor. And the most commonly test means of researches include thermocouple measurement, laser measurement and acoustic measurement. The influence on the temperature field can be improved by changing the installation number or installation position of the atomizing mechanism. Distribution law of air flow in combustor is mainly to adjust the mixing holes or flow distribution of the cyclone. When the area of the mixing hole increases, the temperature field generally improves. The design of the combustor wall is very important for the annular radial-axial combustor and the reflux combustor, because it mainly controls the flow jet direction.

关 键 词：燃烧室 温度场 调试 型面规律 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]