级间燃烧室在航空发动机上应用分析

毛艳辉; 刘存喜; 刘富强; 房爱兵; 徐纲

级间燃烧室在航空发动机上应用分析

毛艳辉^1,2,
刘存喜^1,2,
刘富强^1,2,
房爱兵¹,
徐纲¹

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

基金项目: 国家重点基础研究发展计划 (2007CB210109)

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出版历程
- 收稿日期: 2011-04-07
- 修回日期: 2011-09-06
- 刊出日期: 2012-03-28

Application of inter-stage turbine burner on aero-engine

1.
Key Laboratory of Light-duty Gas-turbine, Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
2.
Graduate University of Chinese Academy of Sciences, Beijing 100190, China

摘要

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.
- 级间燃烧室 /
- 混排涡扇 /
- 热力循环 /
- 非理想循环 /
- 加力燃烧室
Abstract: 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 different from the computation based on ideal cycle and it shows that thrust specific fuel consumption increases almost the same extent as the specific thrust after using inter-stage turbine burner on subsonic flight and specific thrust increases about 10% on supersonic;the economic 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.
- inter-stage turbine burner /
- mixed-exhaust turbofan /
- thermodynamic cycle /
- non-ideal cycle /
- after burner

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参考文献(16)

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