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.
A flight test has been performed on turbofan engine to get the pressure and distortion with lip width of 1.0 mm and 1.5 mm from different and velocities. The data show that during the process from maximum rating augmentation rating, the static pressure diff face will become larger, the quicker of the velo crease of the pressure difference become faster; ence plays distortion an most important role in and the pressure differenc city and the thinner o the data still show th litter＇s static ght altitudes the splitter, the in at the pressur the splitter＇s distortion, the relationship curve e has been given in this paper. e differ- between
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期508-512,共5页
Journal of Aerospace Power
