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对CDA压气机直叶栅和具有不同流向位置和不同几何参数的端壁翼刀叶栅内三维粘性流场进行了数值模拟。结果表明,端壁翼刀主要通过阻断马蹄涡压力面分支汇入通道涡和有效产生反向翼刀涡来控制二次流。加装在距叶片压力面30%节距处且高度为1/3来流附面层厚度、占据前3/4流道的翼刀布置方式为本文所给出的最佳翼刀位置。
The 3D viscous flow field in the cascades of CDA compressor straight blade cascades with different flow direction positions and geometric parameters is simulated. The results show that the endwall wing knife controls the secondary flow mainly by blocking the branch of the pressure distribution of the horseshoe vortex and entering the passageway vortex and effectively generating the reverse wing blade vortex. The installation of the blade at 30% pitch away from the pressure surface of the blade and the height of 1/3 is the thickness of the flow boundary layer, which occupies the first three-fourths flow channel.