| 间冷回热航空发动机性能计算与分析 |
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| 引用本文： | 龚昊,王占学,康涌,黄红超,李刚团.间冷回热航空发动机性能计算与分析[J].航空动力学报,2014,29(6):1453-1461. |
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| 作者姓名： | 龚昊 王占学 康涌 黄红超 李刚团 |
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| 作者单位： | 西北工业大学 动力与能源学院, 西安 71007;西北工业大学 动力与能源学院, 西安 71007;中国航空工业集团公司 中国燃气涡轮研究院, 成都 610500;中国航空工业集团公司 中国燃气涡轮研究院, 成都 610500;中国航空工业集团公司 中国燃气涡轮研究院, 成都 610500 |
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| 基金项目： | 工业和信息化部民用飞机专项科研项目（MJ-D-2011-10） |
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| 摘 要： | 在常规循环双轴分排大涵道比涡扇发动机模型基础上,通过引入间冷器、回热器和间冷涵道模型,发展了间冷回热航空发动机(IRA)性能模拟方法.编写了相应的性能计算程序,计算并分析了一种间冷涵道独立排气的IRA的高度速度特性和节流特性.计算表明:全包线内,回热器一直可以正常换热,IRA可以正常工作.不同工况下,IRA的净推力都接近或大于对照常规循环涡扇发动机,而耗油率较对照常规循环涡扇发动机降低9%~20%.
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| 关 键 词： | 间冷 回热 航空发动机 性能模拟 发动机特性 |
| 收稿时间： | 4/9/2013 12:00:00 AM |
Performance calculation and analysis of intercooled recuperated aero-engine |
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| GONG Hao,WANG Zhan-xue,KANG Yong,HUANG Hong-chao and LI Gang-tuan.Performance calculation and analysis of intercooled recuperated aero-engine[J].Journal of Aerospace Power,2014,29(6):1453-1461. |
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| Authors: | GONG Hao WANG Zhan-xue KANG Yong HUANG Hong-chao and LI Gang-tuan |
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| Institution: | School of Power and Energy, Northwestern Polytechnical University, Xi'an 71007;School of Power and Energy, Northwestern Polytechnical University, Xi'an 71007;China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China;China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China;China Gas Turbine Establishment, Aviation Industry Corporation of China, Chengdu 610500, China |
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| Abstract: | In combination with intercooler, recuperator and intercooler duct model, an intercooled recuperated aero-engine(IRA) performance simulation methodology was developed based on conventional cycle two-spool unmixed flow high bypass ratio turbofan engine model. And an IRA performance calculation program was compiled. The characteristics of the IRA with separate intercooler duct exhaust were calculated and analyzed for the altitude velocity and throttling. The results indicate that, heat exchange process of the recuperator can always take place and IRA can operate normally in the flight envelope. In different conditions, the net thrust of the IRA is close to or higher than that of the conventional turbofan engine, while the specific fuel consumption of the IRA is reduced by 9% to 20%. |
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| Keywords: | intercooled recuperated aero-engine performance simulation engine characteristic |
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