Off-Design Prediction of Transonic Axial Compressors: Part 2 — Generalized Mean-Line Loss Modelling Methodology
In Part 1, of this two-part paper, an off-design mean-line code and a generalized methodology to obtain “tuning” factors were presented. It was shown that the modified factors were capable of predicting the off-design performance of four well documented NASA transonic axial compressors. In this paper, Part 2, a generalized methodology to create correlations for the rotor and stator total pressure losses, deviation angles, and blade row inlet and exit blockage factors is presented. The generalized mean-line loss modelling methodology will allow the compressor designer to decommission the use of the performance map scaling techniques. In its place, the generalized predictive methodology will accurately estimate the off-design performance of transonic axial compressors and can be used to fill the gaps of missing data.