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research-article

Simulation of Multi-stage Compressor at Off-Design Conditions

[+] Author and Article Information
Feng Wang

Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, UK
feng.wang@eng.ox.ac.uk

Mauro Carnevale

Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, UK
mauro.carnevale@eng.ox.ac.uk

Luca di Mare

Osney Thermo-Fluids Laboratory, Department of Engineering Science, University of Oxford, UK
luca.dimare@eng.ox.ac.uk

Simon Gallimore

Rolls-Royce plc, Derby, UK
simon.gallimore@rolls-royce.com

1Corresponding author.

ASME doi:10.1115/1.4038317 History: Received September 18, 2017; Revised September 27, 2017

Abstract

Computational Fluid Dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multi-stage, high-speed machines remain challenging. This paper presents the authors' effort to improve the reliability of CFD in multistage compressor simulations. The endwall geometry features are meshed with minimal approximations. Turbulence models with linear and non-linear eddy viscosity models are assessed. The non-linear eddy viscosity model predicts a higher production of turbulent kinetic energy in the passages, especially close to the endwall region. This results in a more accurate prediction of the choked mass flow and the shape of total pressure profiles close to the hub. The non-linear viscosity model generally shows an improvement on its linear counterparts based on the comparisons with the rig data. For geometrical details, truncated fillet leads to thicker boundary layer on the fillet and reduced mass flow and efficiency. Shroud cavities are found to be essential to predict the right blockage and the flow details close to the hub. At the part speed the computations without the shroud cavities fail to predict the major flow features in the passage and this leads to inaccurate predictions of massflow and shapes of the compressor characteristic. The paper demonstrates that an accurate representation of the endwall geometry and an effective turbulence model, together with a good quality and sufficiently refined grid result in a credible prediction of compressor matching and performance with steady state mixing planes.

Rolls-Royce plc
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