某型分区供油喷嘴的热防护特性试验  

Experiment on thermal protection characteristics of a partition fuel supply nozzle

作　　者：张净玉[1] 郑媛 杨治 孙玉奇[1] 何小民[1] ZHANG Jingyu;ZHENG Yuan;YANG Zhi;SUN Yuqi;HE Xiaomin(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2021年第5期969-976,共8页Journal of Aerospace Power

摘　　要：针对多级旋流燃烧室供油系统热防护问题,开展了某型分区供油喷嘴热防护特性试验研究,获得了不同来流气动参数和燃油参数下喷嘴壁温分布。结果表明:随着燃油进口温度、进气温度的升高喷嘴各测点壁温均升高,其中集油环油路外壁温度与进口油温增加幅度基本一致,喷嘴外壳壁温与进气温度增加幅度基本一致;集油环油路外壁、集油环外壳在主油路关闭后壁温升高;集油环油路外壁壁温低于喷嘴外壳最高达到300 K,空气隔热屏结合"油路互冷"方案的热防护效果显著。For the problem of thermal protection of fuel supply system in multi-stage swirl combustion chamber, the thermal protection characteristic experiment of a partition fuel supply nozzle was carried out, and the wall temperature distribution of the nozzle under different aerodynamic and fuel parameters was obtained. The results showed that the wall temperature of each measuring point of the nozzle increased with fuel inlet and air inlet temperature, the outer wall temperature of the fuel collecting ring was basically consistent with the increment of fuel inlet temperature, and the wall temperature of the nozzle casing was basically consistent with the increment of air inlet temperature. The temperature of outer wall of the fuel collecting ring and the casing of the fuel collecting ring rose when the main fuel was closed;the temperature of the outer wall of the fuel collecting ring was lower than that of the nozzle casing to a maximum of 300 K, and the thermal protection effect of the air heat shield combined with "fuel intercooling" was significant.

关 键 词：热防护 燃烧室 分区供油喷嘴 供油系统 壁温分布 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]