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DONBAR J,POWELL O,GRUBER M,JACKSON T.Post-test analysis of flush-wall fuel injection experiments in a scramjet combustor[R].AIAA 2001-3197. 张鹏;俞刚.;超燃燃烧室一维流场分析模型研究[J]
Researchers have done much research for different combustor configurations.The configuration with backwind step is widely adopted in the design of scramjet combustor. 以往国内外的研究工作者对不同结构的燃烧室进行了大量研究,其中突扩型结构是主流的设计思想之一。
First,hydrogen-air scramjet combustor is numerically simulated and analyzed by solving the general one-dimensional unsteady Euler equation. Second,compressible,reacting,turbulent flow solutions are obtained. 通过求解广义一维非定常Euler方程，数值模拟了氢燃料的燃烧室，并和实验结果进行了比较和分析。
Then the flow fields of scramjet combustor with fix geometry and isolator are simulated at different inflow Mach number and the influence of direction of injection fuel to flow structure are analyzed. 在此基础上对固定几何、带隔离段的双模态超燃冲压发动机在不同飞行马赫数下的流场进行了模拟，最后分析了不同的燃料喷射方向对燃烧室和隔离段流场的影响。
Abstract A numerical study of the cold flowfield of a hydrocarbon fueled model scramjet combustor have been completed with the NUMECA, which is a famous computational fluid dynamic software . 摘要超声速燃烧一直以来被视为人类采用吸气式推进器实现高超声速飞行的最关键的技术难题之一。
Influence of Injection Mode on Flame Stability in Dual-mode Scramjet Combustor 喷注方式对双模态冲压发动机燃烧稳定性的影响
Analysis of Comparative Numerical Simulation of Free-jet Scramjet Combustor 自由射流超燃冲压发动机燃烧室流场对比计算研究
Experimental Investigation of Hydrocarbon-fuel Ignition in Scramjet Combustor 超音速燃烧室碳氢燃料点火实验研究
Numerical Simulation of the Flowfield in a Scaled down Scramjet Combustor 超燃冲压发动机缩比燃烧室流场数值模拟
Issues associated with long duration high enthalpy scramjet combustor testing 高焓超音速燃烧冲压喷气发动机燃烧室长期试验的结果
Experimental investigation of ignition technology in liquid hydrocarbon fueled scramjet combustor 碳氢燃料超燃冲压发动机点火技术试验
Effects of Fuel Injection Scheme on the Mixing and Combustion Efficiency of a Scramjet Combustor 燃料引射方式对超燃冲压燃烧室混合及燃烧效率的影响
Numerical study of the cold flowfield of a hydrocarbon fueled model scramjet combustor with a streamwise vortices mixer 碳氢燃料流向涡掺混超燃模型燃烧室冷态流场数值研究
and the thrust force increment and CII are controlled efficiently.This work lays a foundation for further study of scramjet combustor control. 对目标推力增益和燃烧室一隔离段交互的控制有效，并为进一步深入研究超燃冲压发动机燃烧室控制问题奠定了基础。
scramjet combustor 超音速燃烧室
Hydrogen injection and scramjet ignition testing. 氢注入及冲压点火测试。
Full-Scalc Liquid Fuel Ramjet Combustor Tests. 全尺寸液体冲压发动机燃烧室试验。
Fig. 2 Schematic of the combustor model. 图2微燃烧器数值模型内部结构。
Keywords Scramjet combustor;Performance analysis;Design parameter analysis;Ignition performance;Combustion performance;Theoretical analysis;Experimental investigation;Numerical simulation; 超燃冲压发动机燃烧室;性能分析;设计参数分析;点火特性;燃烧性能;理论分析;试验研究;数值模拟;
The scramjet supersonic combustor and its test facility have been designed by enthalpy method and characteristic line method. 采用热焓法、特征线法等进行了超音燃烧室试验器的计算和设计工作。