Abstract: Based on the operation characteristics of Solid Propellant Air Turbo Rocket (SP-ATR)，new operation mode to realize the afterburning of SP-ATR based on the two independent gas generators was proposed. Series of study were carried out mainly by the numerical and experimental methods focusing on the aerodynamic design of compressor and turbine and the integration of turbocharger，through which the characteristics map of turbocharger was calculated by numerical simulation and performance verified by the cold flow experiments. The studies on mixed combustion between the low temperature and swirling gas by driving the turbine and air and fuel rich gas were carried out，in which the influences on combustion efficiency by different factors were studied，such as rotation speed of turbine，jet angle of the inlet air，the flux of fuel rich gas in the afterburner，jet position of fuel rich gas，and so on，that determined principle prototype and the scheme and layout form of the key components. Finally，the hot firing experiments were carried out，through which the SP-ATR based on two independent gas generators operation principle was examined，the turbocharger was tested to be safe and reliable and the performance of turbocharger could meet the design requirement，that the compressor pressure ratio was 3.3，the rotation speed was 82kr/min，and the combustion efficiency was 85.21%.

Key words: Solid Propellant Air Turbo Rocket (SP-ATR)，Compressor，Turbine，Turbocharger

摘要： 针对固体燃料空气涡轮火箭发动机(SP-ATR)的工作特点，提出了双燃气发生器的加力工作模式，并根据总体性能要求确定了部件的工作参数。主要采用数值模拟和实验研究相结合的手段，分别针对压气机和涡轮部件开展了气动设计和增压装置集成，获得了工作特性，并完成了增压系统工作特性的冷流实验验证。开展了考虑涡轮后低温旋流条件下多股气流的高效掺混燃烧研究，通过研究涡轮转速、空气入射角度、补燃室富燃燃气流量和富燃燃气射流位置对燃烧效率的影响，确定了原理样机和关键部件的恰当形式和布局方式。最终开展了原理样机的地面热试实验，验证了双燃气发生器的SP-ATR发动机的工作原理，热试实验结果表明燃气涡轮增压装置工作可靠，性能满足设计要求，其中压气机压比达到了3.3，转速为82kr/min，补燃室燃烧效率为85.21%。

关键词: 固体燃料空气涡轮火箭发动机；压气机；涡轮；燃气涡轮增压装置