压气机盘腔径向引流减涡器研究综述

Review of Vortex Reducer in Radial Inflow of Compressor Disk Cavity

径向引流减涡器通常位于航空发动机压气机盘腔中,通过抑制气流周向速度的发展从而降低空气系统引气过程中的压力损失,对于提升发动机效率有着十分重要的作用。本文对压气机盘腔径向引流减涡器的相关研究进行综述。研究表明:常用的减涡器包括减涡管、去旋喷嘴、翅片和导流板等结构。其中,管式减涡器的研究和应用最多,其减阻效果较好,但存在着质量较大,且在高速旋转时易产生振动等问题;去旋喷嘴质量较轻,但也有着流量不稳定的现象;导流板同样有着安装和稳定上的问题。有学者尝试对减涡管和去旋喷嘴的结构进行改进,均取得了一定的优化效果。通过对现有研究的梳理可以发现:目前还缺乏描述总压损失的理论模型,熵分析可以作为新的入手点研究总压损失机理。近期研究表明总压损失主要出现在转折位置,这一点与静压损失有所不同,也为减涡器的改进优化提供了思路。

The vertex reducer located in the compressor disc cavity can reduce the pressure loss of the air system during the process of radial inflow by suppressing the tangential velocity of the air.It plays an important role in improving the efficiency of the engine.At present,the vortex reducers mainly include tube,de?swirling nozzle,fin and baffle.The tubed vortex reducer has the most research and application.But there are some problems,such as large mass and vibration in high?speed rotation.The mass of the de?swirl nozzle is less,but there is also a phenomenon of flow instability.The baffle also has the problems of installation and stability.Some scholars have tried to improve the structure.However,in the current research,there is no theoretical model to describe the total pressure loss.Entropy analysis can be used as a new way to study the mechanism of total pressure loss.Recent studies show that the total pressure loss mainly occurs at the turning point,which is different from the static pressure loss,and also provides ideas for the optimization of the vortex reducer.