Numerical investigation of tip clearance effects in an axial transonic compressor |
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Authors: | R Ciorciari A Lesser F Blaim R Niehuis |
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Affiliation: | 1. Institute for Jet Propulsion, University of Federal Armed Forces Munich, Werner-Heisenberg-Weg 39, D-85577, Neubiberg, Germany
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Abstract: | Numerical investigations of the Darmstadt transonic single stage compressor (DTC), in the Rotor1-Stator1 configuration, aimed
at advancing the understanding of the effect of different rotor tip gaps and transition modelling on the blade surfaces are
presented. Steady three dimensional Reynolds Averaged Navier Stokes (RANS) simulations were performed to obtain the flow fields
for the different configurations at different operating conditions using the RANS-Solver TRACE. The stage geometry and the
multi-block structured grid were generated by G3DMESH and a grid sensitivity analysis was conducted. For the clearance gap
region, a fully gridded special H-grid was chosen. Comparisons were made between the flow characteristic at design speed,
representative for a transonic flow regime, and at 65% speed, representative for a subsonic flow regime. The computations
were used to analyse the flow phenomena through the tip clearance region for the different configurations and their impact
on the performance of the compressor stage. |
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Keywords: | Flow in axial compressor surge and stall tip clearance flow multimode transition model |
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