Special aspects of numerical simulation of a two-stage axial-flow compressor with defective blades

Abstract

The paper presents the results of a stage of development of an analytical model for assessing the impact of various defects on the operation of an axial-flow compressor. Some recommendations on setting the numerical models for carrying out gas dynamic and strength analysis of compressor stages and blades with account for various defects are proposed. Verification was carried out for the models presented: the results are also presented in the paper. On the basis of the verification results some special aspects of CFD-modeling are discussed. The requirements for the defects under investigation are defined. A classification of the defects that can be analyzed with the use of the developed mathematical description of the geometry of airfoils and blades with account of all proposed recommendations for the setting of the numerical model is presented.

Keywords

• gas turbine
• gas turbine engine
• axial-flow compressor
• blade row
• blade defects
• computational fluid dynamics