摘要
通过ATR发动机总体性能仿真,研究了加力式ATR发动机特性。将燃气发生器及补燃室的热力计算模块集成到压气机与涡轮的共同工作点非线性气动热力模型中,计算考虑了变比热容影响。仿真结果表明,注入加力推进剂可有效提高发动机比推力,但比冲会降低;加力ATR发动机性能与设计点参数、设计点有无加力及加力推进剂流率大小有关;发动机需精心匹配,以保证补燃室内二次燃烧的混合气组分有较高的焓值和合适的余氧系数,从而获得较高的发动机性能。在非设计点上,对于调节计划为相对转速不变的加力ATR发动机而言,在尾喷管喉部面积不变时,需同时调节涡轮燃气发生器和加力推进剂流量,发动机为双变量控制。
The thermodynamic model of air turbo rocket（ATR） was built and the performances of ATR in augmented mode were simulated at design-and off-design points.In the model,the co-operating of the compressor and turbine was integrated with the thermo-chemical calculations for the gas generator and the afterburner,and variant thermal properties were considered with temperature and composition of gas mixture.The results show that the specific thrust increases when extra propellant is added into the afterburner,meanwhile the specific impulse decrease on the contrary.Besides on the component design parameters,the engine performances in augmented mode depend also on which mode,dry or augmented one is applied at design point,and how much the propellants are supplied into the afterburner.The engine operating point is suggested to be well matched in order to obtain a gas mixture in the afterburner having high enthalpy and desired equivalence ratio,and to improve the engine performance.If the compressor shaft speed as percent of design is held constant in the engine control mode,the augmented ATR is then controlled for the fixed geometry nozzle by adjusting the mass flow rates of both propellants： to drive the turbine and to augment thrust.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期650-655,共6页
Journal of Solid Rocket Technology
基金
国家863项目(2010AA7050303)
