级间燃烧室在航空发动机上应用分析  

Application of inter-stage turbine burner on aero-engine

作　　者：毛艳辉[1,2] 刘存喜[1,2] 刘富强[1,2] 房爱兵[1] 徐纲[1] 

机构地区：[1]中国科学院工程热物理研究所轻型动力重点实验室,北京100190 [2]中国科学院研究生院,北京100190

出　　处：《航空动力学报》2012年第3期578-587,共10页Journal of Aerospace Power

基　　金：国家重点基础研究发展计划(2007CB210109)

摘　　要：采用F100-PW229的参数,对发动机增设级间燃烧室后进行了非理想循环分析,比较了不同马赫数下级间燃烧室与加力燃烧室的性能差异,分析了部件效率对带级间燃烧室发动机性能的影响,对比了主燃烧室、级间燃烧室、加力燃烧室的燃烧效率;计算结果与理想循环存在差异:亚声速下,级间燃烧室发动机推力的增加需要相近增量的耗油率,超声速下同等耗油率可增加约10%推力;其经济性、机动性介于常规发动机和带加力燃烧室发动机之间;最后对增设级间燃烧室的发动机进行了参数优化.The engine with inter-stage turbine burner was computed in non-ideal cycle with F100-PW229 parameter. The differences of performance and thermal efficiency between inter-stage turbine burner and afterburner were compared; effect of component efficiency on the engine with inter-stage turbine burner was analyzed; combustion efficiency of main burner, inter-stage turbine burner, and after burner were contrasted. The result was dif- ferent from the computation based on ideal cycle and it shows that thrust specific fuel con sumption increases almost the same extent as the specific thrust after using inter-stage tur- bine burner on subsonic flight and specific thrust increases about 10~ on supersonic; the e conomic performance is worse than base engine, and maneuverability is worse than engine with after burner. Then, the parameter of inter-stage turbine burner engine was optimized.

关 键 词：级间燃烧室 混排涡扇 热力循环 非理想循环 加力燃烧室 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]