压气机紧凑S形过渡段内周向弯静子性能数值计算

为了合理利用叶片周向弯提升紧凑S形过渡段内静子的气动性能,以某压缩系统过渡段内的静子为研究对象,利用3维计算软件对S形过渡段内采用不同周向弯的静子在设计Ma可用攻角范围内的性能进行数值计算。结果表明:气动负荷是控制静子叶片损失的主要因素,叶片周向弯改变了负荷的径向分布,叶片根部正弯使根部气动负荷减小,根部性能明显改善;低能流体径向迁移也是影响叶片损失的重要因素。相对于直叶片,L形叶片最小损失减小48.5%,且低损失攻角范围较宽,可以增大压缩系统的喘振裕度,提升航空发动机性能水平。

Numerical Calculation of Circumferential Curved Stator Performance in Aggressive S-shaped Transition Duct of Compressor

In order to improve the stator aerodynamic performance within aggressive S-shaped transition duct by using the vane circumferential curve reasonably,taking the stator in the transition duct of a compression system as the research object,the numerical calculation of performance with different circumferential curved stator in the design Ma available incidence in the S-shaped transition duct was carried out by three-dimensional calculation software.The results show that the main factor of controlling the loss of stator vane is aerodynamic load.The radial distribution of the load is changed by the vane circumferential curve,and the aerodynamic load of the endwall is reduced by the positive curve of the vane endwall.The endwall performance is obviously improved.The radial migration of low energy fluid is also an important factor affecting stator loss.Compared with the straight blade,the minimum loss of L blade is reduced by 48.5%,and the range of low loss incidence is wide,which can improve surge margin of compression system and aeroengine performance.