摘要
利用流场计算结果建立了反映飞行马赫数、攻角、斜板角度和风扇进口静压影响的超声速进气道多维实时数学模型。综合该进气道模型、某型涡扇发动机实时数学模型和实时喷管模型,建立了实时的推进系统数学模型。利用此模型研究了飞行马赫数、攻角、斜板角度和出口反压对涡扇发动机工作参数的影响。结果表明,该模型准确度高,实时性好,可完成推进系统的动静态过程仿真计算;并可用于进气道与发动机的匹配以及超声速进气道控制研究。
The supersonic inlet model is established with four variables namely Mach number, angle of attack, slope angle and exit pressure according to the results of the 3D full flow field numerical simulation. Integration the inlet model, turbo fan and nozzle real time model forms the real time model of propulsion system. Effects of Mach number, angle of attack ,slope angle and exit pressure on the propulsion system are investigated with the model. Simulation results show that the real time model of propulsion system is a real time model which is accurate enough to calculate both the steady and transient process, and to study match of inlet and engine as well as the control of inlet.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2006年第3期266-269,共4页
Journal of Propulsion Technology
基金
西北工业大学青年教师创新基金资助项目(08250207)
