叶顶间隙对压气机气动性能影响的数值研究  

Numerical Simulation of Effects of Tip Clearance on Axial Compressor Aerodynamic Performance

作　　者：罗响午 余又红[1] 李钰洁[1] 

机构地区：[1]海军工程大学动力工程学院,武汉430033

出　　处：《热力透平》2015年第1期62-66,共5页Thermal Turbine

基　　金：国家部委基金资助项目(4010303010402)

摘　　要：叶顶间隙影响着轴流式压气机性能的提高,通过三维定常数值模拟计算研究了压气机动叶顶部间隙尺寸对其总体性能、间隙流场参数以及流场损失分布的影响。研究发现:间隙尺寸增大对压气机总体性能影响显著,间隙尺寸的增大改变了动叶叶栅通道上部的流场结构,并影响该区域熵增分布,随着间隙增大该区域熵增变大,间隙较大时,该区域熵增速度加快,同时间隙尺寸的增大导致下一排静叶的进气条件恶化,使得压气机整级做功能力下降。所得结论可为压气机叶顶间隙高度控制提供理论参考。The influence of the blade tip clearance size of compressor rotor on the aerodynamic performance and the loss distribution of the compressor were investigated by numerical simulation.Results show that the aerodynamic performance decreases markedly due to the increase of tip size.The analyses of the rotor flow field indicate that a big influence will appear as the increase of the tip clearance size.The enlarged tip clearance will change the flow structure in the upper passage of the rotor,and influence the entropy generation in this region obviously.With the increase of tip clearance size,it will lead to the increase of entropy generation and result in the deterioration of inlet flow conditions in next stator,thus reducing the working ability of the compressor.The obtained results can provide theoretic reference for compressor tip clearance design.

关 键 词：轴流压气机 数值模拟 间隙涡 熵增 

分 类 号：TH45[机械工程—机械制造及自动化]