【摘要】 目前针对涡轮钻具叶片径向厚度分布的研究较为欠缺。为此，基于CFD方法，以贝塞尔曲线造型方法生成的叶片型线为基础，设置叶片顶部至叶根处2种厚度变化不同的叶型，采用等比例缩放的形式进行叶片造型，通过数值模拟并与普通弯扭叶片的涡轮钻具进行对比分析，研究变截面叶片对涡轮钻具性能的影响。研究结果表明：改进后的叶片1结构在100～2 000 r/min转速范围内所能承受的扭矩相比于等厚叶片结构增大了21%,但压降总体高出等厚叶片结构6.6%;叶片2结构相比于等厚叶片所能承受的扭矩增大了18.3%,但压降升高了12.3%;改进后的2种叶片结构最高效率可达71.75%和71.83%,相比等厚叶片结构有显著提升。研究结论可为高性能涡轮钻具叶片的设计提供理论参考。更多还原

【Abstract】 The radial thickness distribution of turbodrill blades has been rarely studied. Based on the computational fluid dynamics(CFD) method and the blade profile generated from Bessel curve modeling method, two blade profiles with different thickness variations from the top to the root of the blade were set. Then, blade modeling was carried out in an equally scaled form. Finally, numerical simulation was conducted and the modelled blades were compared with conventional twisted blade turbodrill to identify the effect of tapered blades on the performance of turbodrill. The study results show that the improved blade 1 structure can withstand 21% more torque than the equally thick blade structure in the speed range of 100 to 2 000 r/min, but the overall pressure drop is 6.6% higher. The improved blade 2 structure can withstand 18.3% more torque than the equally thick blade structure, but the pressure drop is increased by 12.3%. The highest efficiency of the improved two blade structures can reach 71.75% and 71.83% respectively, which is significantly higher than that of the equally thick blade structure. The conclusions provide theoretical reference for the design of high performance turbodrill blades.更多还原