不同冷却结构对涡轮冷却叶片温度分布特性影响研究  

Study on the Influence of Different Cooling Structures on the Temperature Distribution of Turbine Cooling Blades

作　　者：程闻笛 

机构地区：[1]宝鸡文理学院机械工程学院,陕西宝鸡

出　　处：《建模与仿真》2019年第3期117-124,共8页Modeling and Simulation

摘　　要：近年来,先进冷却技术得到了迅猛发展,先进冷却结构能够实现对涡轮叶片高效冷却降温,显著提升涡轮冷却叶片力学性能,为探索高效冷却结构叶片,最大程度的使涡轮冷却叶片保持在较低的工作温度下,维持低温状态下高温镍基合金材料叶片优异的力学性能,本文运用ANSYS Fluent数值模拟计算方法对两种不同冷却结构涡轮叶片分别展开温度分布特性研究,寻找最优冷却结构的涡轮冷却叶片。结果表明:3孔式涡轮叶片整体冷却降温效果明显优于9孔式涡轮冷却叶片;冷却孔体积增大可以扩大涡轮冷却叶片冷却通道内部的气体流量,改善叶片整体冷却效果,在一定程度上提高叶片力学性能。In recent years,advanced cooling technology has developed rapidly.The advanced cooling struc-tures can achieve efficient for turbine cooling blades and improve the mechanical properties of blades remarkably.In order to explore efficient cooling structures of turbine blades,keep the tur-bine cooling blade working at a low temperature to the maximum extent,and keep the mechanical properties of High temperature nickel base alloy material blades when at the low temperature.In this paper,the temperature distribution characteristics of turbine blades with two different cooling structures were studied by using ANSYS Fluent numerical simulation method to find the optimal cooling structure.The results show that the cooling effect of 3-hole turbine blade is significantly better than that of 9-hole turbine blade.The increase of cooling hole volume can enlarge the gas flow in the cooling passage of turbine cooling blades,improve the cooling effect of blades,and improve the mechanical properties of blades to some extent.

关 键 词：冷却结构 涡轮叶片 高效冷却 温度分布 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]