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Wall-Modeled Large-Eddy Simulations of a Multistage High-Pressure Compressor

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Abstract

This study aims at evaluating the feasibility and the accuracy of a Wall-Modeled Large Eddy Simulation of an actual aeronautical multistage axial high-pressure compressor. The computational domain is composed of 37 blades and a geometrically complex recirculating cavity. The numerical method TurboAVBP is able to handle such a technical challenge thanks to its unstructured and massively parallel approach as well as dedicated rotor-stator interface treatments. The influence of grid resolution, from less than 100 millions to more than 1 billion of cells, is particularly evaluated. The intermediate grid correctly predicts the global aerodynamic performances up to the lowest mass flow rate regime. In comparing with time-resolved measurements, the finest grid is shown to accurately predict flow within rotors, especially in their tip regions that are critical for performances and stability of the whole compressor.

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Acknowledgements

The authors acknowledge the financial support of Safran within the Numerical Core 2020 project. This work was granted access to the HPC resources of CINES under the allocation x20162a6074 made by GENCI. The authors are grateful to X. Ottavy and J. Schreiber (LMFA) for fruitful discussions on CREATE.

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Correspondence to Jerome de Laborderie.

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de Laborderie, J., Duchaine, F., Gicquel, L. et al. Wall-Modeled Large-Eddy Simulations of a Multistage High-Pressure Compressor. Flow Turbulence Combust 104, 725–751 (2020). https://doi.org/10.1007/s10494-019-00094-0

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Keywords

  • Turbomachinery
  • Axial compressor
  • Large-Eddy simulation
  • High-performance computing