The Design Analysis of the Damaged Compressor Blade Impact on the Aerodynamic Parameters

Abstract

Abstract The research is about the traditional approach in defects assessment, like damages in aviation engine blades and problems in their further use based on the defects analysis not in one blade or stage but in the multistage compressor as a whole. When an airplane is in operation there can be incidents: birds in flight and a small stones and different metal object on the ground. When they penetrate into the engine, the fan’s blades are damaged. The software that simulates geometry model of blade damages has been developed. The calculation model of the damaged blade has been developed on the basis of real engine compressors. The calculation model of the compressor covers procedures for mesh generation and CFD code calculations. This model has been verified by experimental data. It has been studied how compressor blades with nicks and bending affect the compressor performance and how compressor map changes. The studies resulted in the following conclusions: -The existing limits on damages size do not cause serious problems in operation. It was confirmed by the calculation result. - As the result of this compressor study, the critical size of blade nicks (more than 4mm or more than 6% blade chord) and bending (more than 0,023b in the leading edge in the circumferential direction) has been identified in terms of aerodynamics.