摘要
文中采用变比热部件法建立了某型涡轮级间燃烧室发动机性能仿真程序,对比分析了风扇增压比、高压压气机增压比、涵道比、涡轮前温度等主要循环参数对涡轮级间燃烧室发动机和常规发动机性能参数的影响。结果表明:这些循环参数变化时,涡轮级间燃烧室发动机单位推力增长幅度较大,耗油率性能变化曲线趋于平缓,发动机综合性能提升,循环参数的可供选择范围变宽。
A performance simulation program for inter-turbine burner（1TB） turbofan engine was made with the variable specific heat components method, the influence of cycle parameters such as fan pressure ratio, compressor pressure ratio, bypass ratio, turbine inlet temperature on engine performance was analyzed comparatively. The result shows that the specific thrust performance of ITB engine is better; the specific fuel consumption curve is toning down with the varied cycle parameters mentioned above, the range which cycle parameters can be selected is wider than that of conventional engine.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第5期152-154,共3页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
APTD项目资助
关键词
航空发动机
涡轮级间燃烧室发动机
循环参数
单位推力
耗油率
aero engine
inter-turbine burner engine
cycle parameters
specific thrust
specific fuel consumption
