空天飞机超燃冲压发动机燃烧室的气动设计

THE AERODYNAMIC DESIGN OF SCRAMJET COMBUSTORS FOR AEROSPACE PLANE

本文首先说明了单级入轨的空天飞机采用超声速燃烧冲压发动机的必要性。采用一维气体流动的关系式分析了超燃冲压发动机燃烧室的性能和气动设计,然后介绍了NASA Langley 研究中心关于超燃冲压发动机燃烧室气动设计研究工作的主要结果,重点介绍了混合、点火和冷却等问题。最后,讨论了超燃冲压发动机燃烧室气动热力学的地面试验技术与计算流体力学方法。根据试验结果与计算结果,分析了典型超燃冲压发动机燃烧室的性能。

The necessity about using supersonic combustion ramjet(scramjet)for the single stage to orb(?)t aerospace plane is demonstrated.The performance and the aerodynamic design of scramjet combustors areanalysed using the relationships of one-dimensional gas flow The pr(?)-mary results of research work about the aerodynamic design of scram-jet combustor at NASA Langley Research Center are introduced.It putsemphasis on mixing,igition and cooling.The technology of the groundtesting and methods of the computational fluid dynamics for aerothermo-dynamics of scramjet combustors are discussed. Based on the results of thecomputation and the testing,the performance of typical scram jet combus-tots is analysed.