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中等涵道比涡扇发动机高空压力畸变试验

彭生红 田金虎 刘冬根 田应维 邝文

彭生红, 田金虎, 刘冬根, 田应维, 邝文. 中等涵道比涡扇发动机高空压力畸变试验[J]. 航空动力学报, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010
引用本文: 彭生红, 田金虎, 刘冬根, 田应维, 邝文. 中等涵道比涡扇发动机高空压力畸变试验[J]. 航空动力学报, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010
Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal of Aerospace Power, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010
Citation: Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude[J]. Journal of Aerospace Power, 2019, 34(6): 1273-1251. doi: 10.13224/j.cnki.jasp.2019.06.010

中等涵道比涡扇发动机高空压力畸变试验

doi: 10.13224/j.cnki.jasp.2019.06.010

Experiment on inlet total pressure distortion of middle-bypass ratio turbofan engine at high altitude

  • 摘要: 基于中等涵道比涡扇发动机结构及其气动稳定性特点,通过该类型某发动机高空压力畸变试验研究,获取了研究对象合理可行的高空压力畸变试验方案设计、畸变装置选取以及数据处理规范,结果表明:在飞行高度小于14 km范围内,飞行高度对稳态综合畸变指数有一定的影响,但影响不明显;有引气/功率分出136 kW条件下,飞行高度为11 km、飞行马赫数为0.8以及飞行高度为14 km、飞行马赫数为0.39时,该中等涵道比发动机最大巡航状态与最大爬升状态在进口综合畸变指数不大于12%时均能稳定工作。

     

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出版历程
  • 收稿日期:  2018-11-06
  • 刊出日期:  2019-06-28

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