Equivalent model for an axial compressor used for aero engines based on 1D and 3D analytical models and performance data

Abstract

This paper proposes a method to generate an equivalent model for predicting compressor performance by correcting a one-dimensional (1D) meanline analysis model based on the results of three-dimensional computational fluid dynamics (3D CFD) and compressor performance at an engine operating point. By comparing the results predicted by the 1D and 3D analysis methods, the compressor operating region and empirical model that needs improvement in the 1D meanline model are identified. As a result, the off-design profile loss model and the model for the incidence angle in the choking condition are selected as models that need improvement; the models are adjusted based on the 3D CFD analysis results. Correction factors for deviation angle, minimum loss incidence angle, and total loss coefficient are proposed. The correction factors are calculated using an iterative method to match the result for the 1D meanline model and the compressor performance at an engine operating point. The method proposed is applied to a three-stage axial compressor used for an aero engine. This confirms that not only compressor performance near the operating point, but also performance near surge and choking, are well predicted.