Abstract
Due to raising demands from aviation industry concerning weight reduction and increased efficiency, compressor front stages of jet engines are designed as blade integrated disks (blisks). However, a major drawback of blisks is that small cracks from foreign object impacts occurring in service may propagate into the whole disk causing burst at worst case which is unacceptable. As a damaged blade of a blisk cannot easily be replaced, there is a need for repair. For example, borescope blisk blending may be applied on-wing to ensure safe on-going operation. To determine best solutions for the blending shape, process integration and optimisation tools are used which modify a parametric model and examine its impact on fatigue criteria by FEM.
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Acknowledgments
The presented work has been performed within the VIT 3 project (Virtual Turbomachinery) partly funded by the Federal State of Brandenburg, Germany, the European Community, and Rolls-Royce Deutschland. Rolls-Royce Deutschland’s permission to publish this work is greatly acknowledged.
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Karger, K., Bestle, D. (2015). Parametric Blending and FE-Optimisation of a Compressor Blisk Test Case. In: Greiner, D., Galván, B., Périaux, J., Gauger, N., Giannakoglou, K., Winter, G. (eds) Advances in Evolutionary and Deterministic Methods for Design, Optimization and Control in Engineering and Sciences. Computational Methods in Applied Sciences, vol 36. Springer, Cham. https://doi.org/10.1007/978-3-319-11541-2_16
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DOI: https://doi.org/10.1007/978-3-319-11541-2_16
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