论文部分内容阅读
为满足固体推进剂涡轮火箭发动机高负荷、高效率、低展弦比涡轮设计要求,对发动机涡轮进行初步设计.采用哈尔滨工业大学编制的叶型编辑程序,设计单级膨胀近似为4的涡轮动静叶叶型,采用NUMECA软件对所设计的涡轮动静叶流场进行数值计算.结果表明:高膨胀比涡轮动静叶整个流道内均出现超音速流动,采用缩放通道可减小激波损失;静叶出口马赫数较高,产生的尾缘激波与相邻叶栅吸力面相交,使吸力面马赫数波动,产生逆压梯度,增大了流动损失;在动叶中,端壁附面层内二次流沿壁面汇聚到吸力面中部,使吸力面中部损失增大.
In order to meet the high load, high efficiency and low aspect ratio turbine design requirements of the solid propellant turbo rocket engine, the preliminary design of the engine turbine was carried out.Using the leaf type editing program compiled by Harbin Institute of Technology, the single-stage expansion of the turbine is approximately 4 The numerical results of the turbulent flow field and the turbulent flow field of the turbomachine blade were calculated by NUMECA software.The results show that supersonic flows occur in the turbulent flow vane and turbulent flow in the turbulent turbine blade, The Mach number of the exit is higher, the generated trailing edge shock wave intersects the suction surface of the adjacent cascade, causing the Mach number of the suction surface to fluctuate, resulting in the reverse pressure gradient and increasing the flow loss; in the moving blade, The secondary flow converges to the middle of the suction surface along the wall so as to increase the loss in the middle of the suction surface.