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在直流式低速风洞试验室内,采用粒子图像测速技术(PIV)对带6排气膜冷却孔的透平静叶在不同吹风比M和不同叶片安装角β下的流场结构进行了测量,并对流场速度和湍动能进行了分析.结果表明:吸力面的速度梯度明显大于压力面,并且随着叶片安装角的减小和吹风比的增大,速度梯度逐渐变大;安装角对气膜的贴壁性有影响,当β=70°时,气膜的贴壁性最好,且吸力面的贴壁性强于压力面;湍动能的最大值位于冷气发生弯曲的上部,即主流与射流掺混的边界;随着安装角的减小,在压力面下游远场出现的湍动能集中区的脉动程度逐渐减弱,当β=70°时达到最小,随着安装角的再度减小,该湍动能集中区在吸力面下游出现并逐渐增大.
In the low-speed wind tunnel test room, the flow field structure of the turbine vanes with 6-vent film cooling holes under different blowing ratio M and different blade mounting angle β was measured by particle image velocimetry (PIV) The velocity field and turbulent kinetic energy are analyzed.The results show that the velocity gradient of the suction surface is obviously larger than that of the pressure surface and the velocity gradient becomes larger with the decrease of the blade mounting angle and the blowing ratio, When β = 70 °, the adhesion of the gas film is the best, and the adhesion of the suction surface is stronger than that of the pressure surface. The maximum of turbulent kinetic energy is located in the upper part of the bending of the cooling air, that is, the mainstream The boundary of turbulent kinetic energy concentrating zone appeared far below the pressure surface. With the decrease of the installation angle, the turbulent kinetic energy concentrated zone in the downstream of the pressure surface gradually weakened, and reached the minimum when β = 70 °. With the decrease of the installation angle, , The turbulent kinetic energy concentration zone appears downstream of the suction surface and gradually increases.