Geometry Scaling Technique For Aerodynamic Redesign Of Multistage Transonic Compressor

Abstract

The aerodynamic design of multi-stage transonic axial-flow compressors plays a critical role in the overall performance of aeronautical engine, gas turbine and industry compression unit. Despite a series of new design methods have been successfully proposed in the research and development of advanced axial-flow compressors, redesign methods are still one of the most effective measures in the development of available advanced products to meet new requirements. In this work, a geometry scaling technique is proposed in which 1D mean-line analysis and 3D parametric geometric modeling are used to define a series of key redesign criteria with as minor variations as possible in the aerodynamic performance compared against the original design. The motivation behind this technique is to develop a CFD validation rig while keep both the aerodynamic performance and CFD prediction accuracy unchanged with reduced partial annulus model. The proposed scaling technique is then verified by the redesign of a 3.5-stage transonic axial-flow compressor with geometry scaling of blade/vane numbers and IGV-rotor-stator axial spacing. The CFD prediction shows that the variation in overall performance of redesigned compressors is generally within one percent, verifying the effectiveness of the proposed scaling technique.