In an attempt to validate a Large Eddy Simulation (LES) approach, computations of a transonic centrifugal compressor with a backswept, unshrouded impeller followed by radial and axial vaned diffusers are performed. A sector composed of one main blade and one splitter blade, two radial diffuser vanes and six axial diffuser vanes is simulated including all the technological effects of the experimental rig. The LES methodology to simulate the rotor/stator configuration is introduced. Emphasis is put on the best trade-off between accuracy of the simulation and affordable CPU cost. A law-of-the-wall boundary condition is used to reduce the mesh size, with a target of y+ around a hundred for all walls except in the tip leakage with y+ around five. Computation of one entire characteristic line is obtained continuously in time: the transient from the flow at rest to the converged points at blockage, peak efficiency, near surge and path to deep surge is computed increasing progressively the outlet pressure as in the experiments. First, LES results are compared to experiments and show excellent agreement both in terms of overall performance and time-averaged internal flow fields previously obtained by Laser Doppler Anemometry. Then, a focus is proposed on the complementary information LES provide in the rotor. The key findings are that contrary to previous URANS studies in this centrifugal compressor, LES capture influential details of the flow structures in the rotor: secondary structures, shock/boundary layer interaction and boundary layer separation at the tip of the impeller. Moreover, it is clearly shown that the tip leakage vortex increases in size and intensity from peak efficiency to surge and becomes much more erratic. Emphasis is put on the causes and consequences of the tip leakage spillage in the neighbouring rotor channels. Pressure fluctuations were also found to increase from peak efficiency to surge downstream the splitter blade leading edge. The whole results finally show that LES with a law-of-the-wall provides excellent results in such a complex case.
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ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition
June 11–15, 2018
Oslo, Norway
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-5100-5
PROCEEDINGS PAPER
Large Eddy Simulations in a Transonic Centrifugal Compressor
Florent Duchaine,
Florent Duchaine
CERFACS, Toulouse, France
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Laurent Gicquel,
Laurent Gicquel
CERFACS, Toulouse, France
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Gabriel Staffelbach,
Gabriel Staffelbach
CERFACS, Toulouse, France
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Nicolas Buffaz,
Nicolas Buffaz
Safran Helicopter Engines, Bordes, France
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Isabelle Trébinjac
Isabelle Trébinjac
Ecole Centrale de Lyon, Lyon, France
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Jérôme Dombard
CERFACS, Toulouse, France
Florent Duchaine
CERFACS, Toulouse, France
Laurent Gicquel
CERFACS, Toulouse, France
Gabriel Staffelbach
CERFACS, Toulouse, France
Nicolas Buffaz
Safran Helicopter Engines, Bordes, France
Isabelle Trébinjac
Ecole Centrale de Lyon, Lyon, France
Paper No:
GT2018-77023, V02BT44A030; 10 pages
Published Online:
August 30, 2018
Citation
Dombard, J, Duchaine, F, Gicquel, L, Staffelbach, G, Buffaz, N, & Trébinjac, I. "Large Eddy Simulations in a Transonic Centrifugal Compressor." Proceedings of the ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. Volume 2B: Turbomachinery. Oslo, Norway. June 11–15, 2018. V02BT44A030. ASME. https://doi.org/10.1115/GT2018-77023
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