1) forward swept blade
掠动叶
1.
The result indicates that the forward swept blade is profitable to controlling the turbulent noise .
通过前掠、后掠以及径向小型轴流风扇转子流场的数值分析 ,研究了掠动叶对转子气动及声学特性的影响及其作用机理 ,并给出了由转子尾缘旋涡脱落而诱发的紊流噪声的声压值分布。
2) curved rotor
弯掠动叶
1.
The unsteady 3D flow fields in a single-stage transonic compressor under designed conditions are simulated numerically to inves- tigate the effects of the curved rotors on the stage performance and the aerodynamic interaction between the blade rows.
研究结果表明:非定常计算条件下,动叶弯掠后的压气机效率仍然获得大幅提高,并且效率的波动幅值同原型压气机相比明显降低,同时动叶改型前后的效率和压比的非定常波动曲线的相位发生了偏差;弯掠动叶下游的静叶前缘区域的顶部和根部的静压扰动幅值减小,中部的则有所增加,整个径向范围内扰动更为均匀;动叶弯掠后,由于弯掠动叶出口的损失分布的变化以及动叶尾迹和二次流在静叶流道中的输运和耗散特性的改变,静叶前缘区域以外的压力面和吸力面不同位置处的静压波动也发生了变化。
2.
The unsteady 3D flow fields in a transonic compressor at design point were simulated numerically to study the effects of the curved rotors on the aerodynamic loading of the blades.
对一单级跨声压气机设计工况采用弯掠动叶前、后的非定常流场进行了数值模拟,深入分析了动叶弯掠对压气机叶片非定常气动负荷的影响。
3) Swept rotor~+
掠动叶+
4) skewed-swept rotating blade
弯掠动叶
1.
The experiments of variable working condition-rotating stall onaerodynamic and aeroacoustic performance of axial fans with radial rotatingblades and skewed-swept rotating blades carried out are dealt with in the pre-sent paper.
具有相同的几何参数和气动参数的两台弯掠动叶和径向动叶轴流试验风机（弯掠动叶弦长在中径处加长20。
2.
The experiments of steady working condition on aerodynamic and aeroacoustic performance of axial fans with conventional (radial )rotating blades and skewed-swept rotating blades carried out are dealt with in the paper.
试验利用两组轴流试验风机，一组为常规动叶的轴流风机，另一组为弯掠动叶的轴流风机，保持它们具有（除弦长外）相同的几何参数和相同的转速（弯掠动叶弦长增加量为20％左右）。
补充资料：变后掠翼飞机(见后掠翼飞机)
变后掠翼飞机(见后掠翼飞机)
swing-wing aircraft
bianhoul位eyi feiii变后掠翼飞机(swing一wing aircran)见后掠翼飞机。
说明：补充资料仅用于学习参考，请勿用于其它任何用途。