The research is about the new approach in assessing traditional defects, like damages in aviation engine blades and problems in their further use. 

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. There are 2 types of the blade damages: nick and bend. It can simulate any of these two damages on the leading and trailing blades edges. 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. Our 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.

 - The critical size of blade nicks and bending has been identified as the result of this compressor study.


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

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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