Engineers in the field of gas turbine engines have devoted a significant amount of experimental and computational effort to studying blade incursions. A joint industry-university research program involving GE Aviation in Cincinnati, Ohio and The Ohio State University Gas Turbine Laboratory has resulted in the development of an experimental facility to produce controlled blade-on-casing incursions at engineconditions.
In this paper, a unique method to determine the blade tip forces during an incursion is presented. The blade is represented as a load moving at constant speed,
imparting both tangential and radial forces to the casing. A moving load finite element method-based approach to determining blade tip forces during a blade-on-casing incursion in an axial compressor is developed. Future work required to use this approach to determine blade tip forces will be discussed.