涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验

史建邦; 姚尚宏; 王玲玲

涡扇发动机全加力状态收油门过程中分流环参数变化的飞行试验

中国飞行试验研究院发动机所, 西安 710089

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出版历程
- 收稿日期: 2011-05-06
- 修回日期: 2011-12-23
- 刊出日期: 2012-03-28

Transient performance of the splitter of turbofan engine from maximum to intermediate thrust in the flight

Engine Department, Chinese Flight Test Establishment, Xi’an 710089, China

摘要

摘要: 通过在飞行条件下对某型涡扇发动机端部厚度分别为1.0mm和1.5mm的分流环静压和变形量进行实时数据采集,得到了不同飞行高度、速度条件下,分流环内外壁面静压值以及分流环的变形量.结果表明:飞机在发动机全加力状态飞行时急收油门过程中,分流环内外壁面静压差值会产生急增,差值增量随飞行速度的增加而增加,分流环厚度越小,增量越大;分流环内外壁面压差是导致分流环变形的主要原因,并给出了该型分流环变形量随压差的变化关系.
- 涡扇发动机 /
- 分流环 /
- 全加力状态 /
- 变形 /
- 飞行试验
Abstract: A flight test has been performed on turbofan engine to get the splitter’s static pressure and distortion with lip width of 1.0mm and 1.5mm from different flight altitudes and velocities.The data show that during the process from maximum rating to minimum augmentation rating,the static pressure difference between the splitter’s inner and outer face will become larger,the quicker of the velocity and the thinner of the splitter,the increase of the pressure difference become faster;the data still show that the pressure difference plays an most important role in the splitter’s distortion,the relationship curve between distortion and the pressure difference has been given in this paper.
- turbofan engine /
- splitter /
- maximum rating /
- distortion /
- flight test

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参考文献(12)

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