高温升燃烧室喷油杆热防护试验研究  

Experimental Investigation on Thermal Protection for Fuel Injector Pole of High Temperature Rise Combustor

作　　者：李建中[1] 袁丽[2] 尚伟[1] 陈坚[1] LI Jian-zhong YUAN Li SHANG Wei CHEN Jian(Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power System, Nanjing 210016, China School of National Defense Engineering, PLA University of Science and Technology, Nanjing 210007, China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,江苏南京210016 [2]中国人民解放军理工大学国防工程学院,江苏南京210007

出　　处：《推进技术》2016年第12期2336-2342,共7页Journal of Propulsion Technology

基　　金：中央高校基本科研业务费专项资金(NS2014019)

摘　　要：为研究高温升燃烧室喷油杆热防护问题,建立高温升燃烧室喷油杆热防护试验系统,设计加工三个不同尺寸隔热屏,探讨了进气温度、进气速度、供油压力、喷油杆布置方式和隔热屏方案等气动和结构参数影响喷油杆壁面温度、换热特性及油道出口燃油温度的变化规律。研究表明:当进气温度为903K,进气速度为36m/s,压力为0.22MPa时,不安装隔热屏的喷油杆出口燃油温度达到的最高温度为435K,随着供油压力增大,燃油出口温度逐渐降低,但最低温度也超过375K。三种方案隔热屏均能够起到对喷油杆的热防护,能够降低喷油杆壁面温度和油道出口燃油温度,考虑热防护效果和结构重量等综合因素,方案二隔热屏效果最佳,燃油出口最高温度不超过388K。To investigate experimentally the thermal protection for the fuel injector pole of a high temperature rise combustor,three different heat shields were designed and the test rig was installed. The effects of the inflow temperature and inlet velocity,fuel supply pressure,fuel injector pole location and heat shields on the wall temperature and heat transfer characteristics of fuel injector pole and fuel temperature at fuel passage exit were investigated. While the inflow temperature,inlet velocity and fuel supply pressure is 903 K,36m/s and 0.22 MPa,respectively,the maximum fuel temperature of fuel injector pole without a heat shield could attain 435 K and the fuel temperature decreased with the increasing of fuel supply pressure,however,the minimum temperature was more than 375 K.The results show that the thermal protection could be realized and the wall temperature of fuel injector pole and fuel temperature at fuel passage exit could be reduced by the three heat shields. For the comprehensive factor of thermal protection efficiency and structure weight,the second heat shield geometry was optimum and the maximum temperature does not exceed 388 K.

关 键 词：高温升燃烧室 喷油杆 热防护 

分 类 号：V235.22[航空宇航科学与技术—航空宇航推进理论与工程]