空气涡轮火箭组合发动机共同工作研究

根据空气涡轮火箭组合发动机工作原理，明确了发动机共同工作条件，建立了发动机共同工作方程，得到了发动机共同工作线，并给出了影响空气涡轮火箭组合发动机共同工作线位置的两个因素:尾喷管喉部面积和涡轮前燃气总温。基于共同工作方程，分析了两因素对发动机共同工作线的影响规律。结果表明:在同一转速线上，随着尾喷管喉部面积或涡轮前燃气总温增大，发动机空气质量流量增大，压气机增压比降低，共同工作线整体向右下方移动；尾喷管喉部面积和涡轮前燃气总温增大或减小使空气涡轮火箭组合发动机共同工作线移动的方向是相同的，但尾喷管喉部面积变化对共同工作线位置移动的影响程度大于涡轮前燃气总温。 

Analysis of co-work for air turbo rocket

Based on the principle of air turbo rocket, the condition, equation and line of co-work and its influence factors were presented. According to the co-working equation, the influence law of area of the throat for nozzle and total temperature of gas at the inlet of turbine on the co-working line was given. The result showed that the mass flow rate of air for the engine increased and the pressure ratio of compressor decreased as the numerical value of area of the throat for nozzle or total temperature of gas at the inlet of turbine increased on the same rotational velocity line, which made the co-working line move toward lower right direction. The influence law of area of the throat for nozzle and total temperature of gas at the inlet of turbine on the co-working line was similar, but the influence effect of area of the throat for nozzle was more obvious.