摘要
针对超燃冲压发动机燃烧室综合性能的测试需求,从取样探针、系统管路及附件选型、测控方案等角度设计了一套六点暂冲式燃气取样系统,成功实现了燃气发生器出口2.0 s和发动机燃烧室出口1.4 s取样。分别测量了燃气发生器出口测量截面Ⅰ和发动机燃烧室出口测量截面Ⅱ的O2、CO、CO2含量,并采用理论温升法推算燃烧室出口温度约为2 121 K。基于暂冲式燃气取样分析,为评估超燃冲压发动机燃烧室性能提供了新的研究思路。
To satisfy the demand of comprehensive performance testing of scramjet engine combustors,a set of six-point intermittent gas sampling system was designed from the perspective of sampling probes,system piping and accessories selection,as well as monitoring and control schemes.The sampling of the gas generator outlet at 2.0 s and the engine combustor outlet at 1.4 s was successful.The O2,CO,and CO2 contents from gas generator outlet test sectionⅠand the engine combustor outlet test sectionⅡwere measured,the theoretical temperature rise method was used to estimate the combustor outlet temperature of about 2121 K.Based on temporary sampling of gas sampling,it provides a new research idea for evaluating performance of scramjet combustor.
作者
张杰
朱涛
王军
蒙正猛
冯大强
ZHANG Jie;ZHU Tao;WANG Jun;MENG Zheng-meng;Feng Da-qiang(AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China)
出处
《燃气涡轮试验与研究》
北大核心
2020年第1期47-53,共7页
Gas Turbine Experiment and Research
