One of the greatest dangers to properly working aircraft engines, apart from human error, is the ingestion foreign objects into the compressor. These objects may be birds, dust, hail, volcanic ash, ice on wings but also aircraft parts or simply garbage. Modern jet engines can suffer major damage from even small objects being sucked into the engine. We want to show how foreign object debris affects the dynamic stress level of a rotor blade. A comparison between an undisturbed engine inlet and one with an ingested foreign object is carried out. The analysis will focus on the first stage compressor blade of an aircraft engine with a partially blocked radial inlet.

The main subject of this paper concerns transferring a CFD analysis pressure field as a surface load to the structural model of a blade.

First a CFD calculation of a nominal and disturbance regime was conducted. In both cases an unsteady pressure was calculated.

Calculations were carried out on a first stage compressor blade. Ansys 12.1 was used to calculate the entire structure. Unsteady CFD calculations used Fluent for a 1.5 stage axial compressor model. A non-viscous flow was used for the numerical calculations. The unsteady forces were calculated on 10 control cross-sections of a rotor blade. The transient results obtained from the CFD calculations were transferred onto a structural rotor blade model using APDL language script.

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