带叶片涡轮盘腔气流增压温降特性数值模拟研究  

Numerical Simulation Study of Pressure and Temperature Drop Characteristics of Turbine Disk Cavity with Internal Blades

作　　者：郝鑫 连文磊[1] 尚登阅 HAO Xin;LIAN Wenlei;SHANG Dengyue(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学,能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2022年第1期42-44,69,共4页Machine Building & Automation

摘　　要：通过在涡轮盘腔内部增加叶片的方式改变盘腔内部流动结构,从而降低旋转系下的相对总温。针对不同叶片结构对涡轮盘腔内部流动的影响开展数值模拟研究。结果表明:叶片叶型结构设计对内部流场的影响较大,旋流比为影响的主要因素,旋流比接近于1时,增压温降效果最好;导流叶片叶型的差异对总温降增压效果的影响明显;叶片进出口半径对预旋系统整体性能有一定影响。The internal flow structure of turbine disk cavity is changed by adding blades in the disk cavity to reduce the relative total temperature under the rotating system,and the numerical simulation study on the effect of different blade structures over the internal flow in turbine disk cavity is conducted.The results show that the design of blade profile has a great influence on the internal flow field,and the swirl ratio is the main factor.When the swirl ratio is close to 1,the effect of pressurization temperature drop is the best.The difference of guide vane profile has obvious influence on the total temperature drop and pressurization effect.The radius of blade inlet and outlet have certain influence on the overall performance of the pre-swirl system.

关 键 词：航空发动机 涡轮盘腔 内部叶片 增压 温降 数值模拟 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程]