| 高推重比航空发动机部件匹配研究 |
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| 引用本文： | 张跃学,李斌,张军峰,叶代勇.高推重比航空发动机部件匹配研究[J].航空发动机,2012,38(1):13-16. |
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| 作者姓名： | 张跃学 李斌 张军峰 叶代勇 |
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| 作者单位： | 中航工业沈阳发动机设计研究所 |
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| 摘 要： | 针对未来高推重比涡扇发动机的高、低压涡轮功分配问题,进行了总体性能设计研究,并与常规布局涡扇发动机进行对比分析,归纳出其设计难点;提出了2种解决途径,即改变压缩系统的结构形式和采用涡轮间燃烧技术。
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| 关 键 词： | 涡扇发动机 总体性能 耗油率 单外涵 双外涵 涡轮间燃烧 |
Investigation on Component Matching of High Thrust-Weight Ratio Aeroengine |
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| Authors: | ZHANG Yue-xue LI Bin ZHANG Jun-feng YE Dai-yong |
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| Institution: | (AVIC Shenyang Engine Design and Research Institute,Shenyang 110015,China) |
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| Abstract: | Aiming at power distribution of future high thrust-weight ratio engine high and low pressure turbine,the general performance design was conducted and compared with that of the conventional turbofan engine,the design difficulties were summarized.Two solutions about changing compression system structure and adopting interstage turbine combustion technology were proposed. |
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| Keywords: | turbofan engine general performance fuel consumption single-bypass double-bypass interstage turbine combustion |
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