Development of a new through flow method for multi-stage axial compressors and validation with experiments and CFD-computations

Abstract

Development and validation of a universal through flow method applicable to design and analysis of compact multi-stage axial compressors will be described. Our method is based on correlations of the open literature which had been evaluated, selected and improved for this purpose. It contains a span wise mixing model to represent the 3D flow structure. For code validation various test cases are considered covering a wide range of application. Finally, the application of the method to analyse a newly-developed 11-stage gas turbine compressor will be demonstrated. The computed results have been compared with detailed test rig experiments. In addition, multi-stage steady-state computations were executed using a calibrated Navier-Stokes solver for 3D turbulent flows. Very good agreements of computed and measured results were achieved. In particular the through flow solver proves to be very accurate and fast in the prediction of compressor characteristics and has been directly used for optimisation of variable guide vane settings during the compressor test.