Investigations on the effect of propellant supplying and nozzle area variation in the starting process of air turbo rocket [空气涡轮火箭发动机起动过程推进剂供应及尾喷管面积变化规律研究]

作者：Zhao W.; Liu L.; Hu B.; Li L.; Zhao Q.^*

来源：Journal of Solid Rocket Technology, 2021, 44(2): 179-187.

DOI：10.7673/j.issn.1006-2793.2021.02.008

• Air turbo rocket
• Compressor surge
• Nozzle throat area
• Starting process

The aim of the determination is to study effects of propellant supplying rate and tail nozzle area in the starting process of the solid propellant air turbo rocket, an engine dynamic model considering varying specific heat and chemical equilibrium was set up based on the volume method. Starting processes of the engine were simulated under different propellant supplying rates, different nozzle throat areas and changing rates of nozzle throat area along with shaft speed, and then the effects of these parameters on starting period and the position of common working line are compared and analyzed. The research results indicate that increasing the propellant supplying rate can reduce the accelerating period of starting process, but the common work line of engine will move towards the compressor surge line. When the nozzle throat area is smaller than that of its design value, the tail nozzle will be blocked, and then causing compressor surge. On that basis, an adjusting method is put forward by adopting a higher propellant supplying rate combined with a enlarging the nozzle throat area along with engine shaft speed increasing, so that the compressor can avoid surging and keep away from the choking boundary. Safe and fast starting process of engine is realized.

• 单位
  中国科学院大学