| 高负荷高通流跨音压气机的研制和应用 |
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| 引用本文： | 王华青,陈矛章.高负荷高通流跨音压气机的研制和应用[J].航空动力学报,2003,18(2):175-180. |
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| 作者姓名： | 王华青 陈矛章 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院,北京,100083 |
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| 摘 要： | 介绍了高负荷高通流跨音压气机的研制和应用,新研制三级低压压气机平均加功量系数为0.319,进口单位迎面流量为191.0kg/m2·s,进口平均Ma为0.676,效率为0.82,进口轮毂比小于0.35。用到发动机上设计点稳定工作裕度为20.67%,使发动机性能提高14.3%。研制经过了设计、试验、工程应用、外场使用全过程,并已经广泛应用,表明新研制压气机在气动设计、方案选择和结构设计上很成功。
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| 关 键 词： | 航空、航天推进系统 高负荷 高通流 压气机 研制和应用 |
| 文章编号： | 1000-8055(2003)02-0175-06 |
| 收稿时间： | 2002/3/11 0:00:00 |
| 修稿时间： | 2002年3月11日 |
Development and Application of a High Load and High Throughflow Transonic Compressor |
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| Institution: | Beijing University of Aeronautics and Astronautics,Beijing100083,China;Beijing University of Aeronautics and Astronautics,Beijing100083,China |
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| Abstract: | The average loading coefficient of the 3 stage LP compressor is 0.319.The mass flow rate per front area is 191.0 kg/m2s.The average axial Mach number is 0.676.Efficiency is 0.82.Rotor inlet hub/tip radius ratio is less than 0.35.The surge margin is 20.67%.The engine thrust is increased by 14.3%.The engine has been experienced conventional ground test,high altitude testbed test and flight test.Extensive application shows that the layout option, gasdynamic design and structural design are very successful. |
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| Keywords: | aerospace propulsion high load high through flow compressor development and application |
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