Impact of Weld Joint on Compressor Blade Performance

作     者：Mesbah, M. Geuzaine, P. Arts, T. Simon, J. F. 

作者机构：Cenaero Turbomachinery Adv Aerodynam Grp B-6041 Gosselies Belgium Von Karman Inst Fluid Dynam Turbomachinery & Prop Dept B-1640 Rhode St Genese Belgium Techspace Aero B-4041 Milmort Belgium 

出 版 物：《JOURNAL OF PROPULSION AND POWER》 (推进与动力杂志)

年 卷 期：2017年第33卷第1期

页      面：276-284页

核心收录：

学科分类：08[工学] 0825[工学-航空宇航科学与技术] 

基　　金：uropean Union research Turbulence and Transition Modeling for Special Turbomachinery Applications Project [FP6-2005-AERO-1-030939] 

主　　题：Compressor Cascade Boundary Layer Thickness Computational Fluid Dynamics Simulation Reynolds Averaged Navier Stokes Flow Conditions Turbulence Models Vortices Freestream Velocity Static Pressure Aspect Ratio 

摘      要：This contribution focused on the analysis of weld-joint effects resulting from the assembly of the blades and disk for the compressor blades. Experiments at the von Karman Institute and computational fluid dynamics simulations at Cenaero were conducted to study the flowfield in a low-pressure high-speed compressor cascade with two weld-joint configurations. Experiments were performed to measure the total pressure loss coefficient for various inlet flow conditions. Reynolds-averaged Navier-Stokes simulations using the k - L turbulence model were carried out. Comparison between the Reynolds-averaged Navier-Stokes solutions and the experiments were made, and the accuracy of the results was investigated. The impact of the weld-joint height and the upstream boundary layer on the losses was studied. In addition, the effect of the weld-joint heights on the growth of the boundary layer was analyzed and presented.