Regions of three-dimensional separations are an inherent flow feature of the suction surface-endwall corner in axial compressors. These corner separations can cause a significant total pressure loss and reduce the compressor's efficiency. This paper uses wall-resolved LES to investigate the loss sources in a corner separation, and examines the influence of the inflow turbulence on these sources. Different subgrid scale (SGS) models are tested and the choice of model is found to be important. The σ SGS model, which performed well, is then used to perform LES of a compressor endwall flow. The time-averaged data are in good agreement with measurements. The viscous and turbulent dissipation are used to highlight the sources of loss, with the latter being dominant. The key loss sources are seen to be the 2D laminar separation bubble and trailing edge wake, and the 3D flow region near the endwall. Increasing the freestream turbulence (FST) intensity changes the suction surface boundary layer transition mode from separation induced to bypass. However, it does not significantly alter the transition location and therefore the corner separation size. Additionally, the FST does not noticeably interact with the corner separation itself, meaning that in this case the corner separation is relatively insensitive to the FST. The endwall boundary layer state is found to be significant. A laminar endwall boundary layer separates much earlier leading to a larger passage vortex. This significantly alters the endwall flow and loss. Hence, the need for accurate boundary measurements is clear.
Skip Nav Destination
Article navigation
February 2017
Research-Article
Numerical Investigation of Three-Dimensional Separation in an Axial Flow Compressor: The Influence of Freestream Turbulence Intensity and Endwall Boundary Layer State
Ashley D. Scillitoe,
Ashley D. Scillitoe
CFD Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Search for other works by this author on:
Paul G. Tucker,
Paul G. Tucker
CFD Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Search for other works by this author on:
Paolo Adami
Paolo Adami
CFD Methods,
Rolls-Royce Deutschland,
Eschenweg 11,
Blankenfelde-Mahlow 15827, Germany
Rolls-Royce Deutschland,
Eschenweg 11,
Blankenfelde-Mahlow 15827, Germany
Search for other works by this author on:
Ashley D. Scillitoe
CFD Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Paul G. Tucker
CFD Laboratory,
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
Paolo Adami
CFD Methods,
Rolls-Royce Deutschland,
Eschenweg 11,
Blankenfelde-Mahlow 15827, Germany
Rolls-Royce Deutschland,
Eschenweg 11,
Blankenfelde-Mahlow 15827, Germany
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 25, 2016; final manuscript received September 9, 2016; published online October 26, 2016. Editor: Kenneth Hall.
J. Turbomach. Feb 2017, 139(2): 021011 (10 pages)
Published Online: October 26, 2016
Article history
Received:
July 25, 2016
Revised:
September 9, 2016
Citation
Scillitoe, A. D., Tucker, P. G., and Adami, P. (October 26, 2016). "Numerical Investigation of Three-Dimensional Separation in an Axial Flow Compressor: The Influence of Freestream Turbulence Intensity and Endwall Boundary Layer State." ASME. J. Turbomach. February 2017; 139(2): 021011. https://doi.org/10.1115/1.4034797
Download citation file:
Get Email Alerts
Related Articles
Scale-Resolving Simulations of Bypass Transition in a High-Pressure Turbine Cascade Using a Spectral Element Discontinuous Galerkin Method
J. Turbomach (March,2018)
Competing Three-Dimensional Mechanisms in Compressor Flows
J. Turbomach (February,2017)
Controlling Corner Stall Separation With Plasma Actuators in a Compressor Cascade
J. Turbomach (August,2016)
Related Proceedings Papers
Related Chapters
Introduction
Design and Analysis of Centrifugal Compressors
Aerodynamic Performance Analysis
Axial-Flow Compressors
Boundary Layer Analysis
Centrifugal Compressors: A Strategy for Aerodynamic Design and Analysis