Procedure for analyzing, manipulating and meshing of compressor blades to simulate their flow

Abstract

During on-wing time of a jet engine deterioration occurs and leads to decreasing component efficiencies. This results in increasing Exhaust Gas Temperature (EGT) and Specific Fuel Consumption (SFC). Thereby, the condition of the High Pressure Compressor (HPC) has a comparatively large influence on these parameters defining overall engine performance. This can be explained by a changing flow field in the HPC due to geometric deviations which may occur during operation. The geometries are influenced by erosion which results in thinner airfoils, changed leading- and trailing edge geometries, shortened airfoils and increasing tip clearance. The objective for future maintenance strategies is to determine the influence of the different wear mechanisms. This can be done by experiments and Computational Fluid Dynamics (CFD). Because of the high number of different mechanisms and locations of deterioration, CFD-calculations seem to be necessary to give a detailed view of the influence of deterioration. In this regard, the following paper will present a developed procedure for analyzing, manipulating and meshing HPC-blades to simulate their flow. Therefore, three different software-routines for the mentioned steps will be shown and explained. Additionally, an example blade will pass through the process and will be manipulated for max. deviation caused by deterioration. At the end, a CFD-calculation of these blades will be carried out and analyzed for its aerodynamic behavior.