超声速模型燃烧室中气化煤油喷注研究  

Investigation of vaporized kerosene injection in a supersonic model combustor

作　　者：俞刚[1] 李建国[1] 赵震[1] 王冬[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《推进技术》2005年第2期97-100,共4页Journal of Propulsion Technology

基　　金：国家自然科学基金 (10232060)

摘　　要：利用直接照相和纹影显示研究了不同预热温度的煤油喷注到静态大气和马赫数2 5的横向气流时射流结构。煤油加热系统可将0 8kg煤油加热到670K和5 5MPa压力。比较4MPa压力下290K^550K不同温度的煤油射流结构可以发现, 550K煤油射流一旦流出立即完全气化, 并且保持贯穿深度基本不变。结果表明: 喷注汽化燃料有可能改善液体碳氢燃料超声速燃烧室的性能, 因为至少省却了雾化和气化过程。The characteristics of jet structure of kerosene injection into quiescent atmosphere and Mach 2.5 crossflow at various preheat temperature were investigated experimentally by using direct photo and schlieren visualization. A heating system was designed and tested that can prepare heated kerosene of 0.8 kg up to 670 K at a pressure of 5.5 MPa. Comparison of kerosene jet structure in the preheat temperature range of 290 K-550 K demonstrated that with injection pressure 4 MPa the jet plume turns into vapor phase completely at injection temperature of 550 K, while keeping the penetration depth essentially unchanged. The results suggest that the injection of vaporized fuel would improve the performance of a liquid hydrocarbon-fueled supersonic combustor because the evaporation process is now omitted.

关 键 词：航空发动机 煤油 射流 超声速燃烧 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]