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Please use this identifier to cite or link to this item: https://dspace.lboro.ac.uk/2134/35725

Title: Improved modelling capabilities of the airflow within turbine case cooling systems using smart porous media
Authors: Li, Yan-Ling
Walker, Alastair Duncan
Irving, John
Keywords: Aerodynamics
Gas turbines
Turbine case cooling (TCC)
Impingement cooling holes
Issue Date: 2018
Publisher: ASME (The American Society of Mechanical Engineers) © Rolls-Royce plc
Citation: LI, Y-L., WALKER, A.D. and IRVING, J., 2018. Improved modelling capabilities of the airflow within turbine case cooling systems using smart porous media. Journal of Engineering for Gas Turbines and Power, 141 (5), 051003.
Abstract: Impingement cooling is commonly employed in gas turbines to control the turbine tip clearance. During the design phase, Computational Fluid Dynamics is an effective way of evaluating such systems but for most Turbine Case Cooling (TCC) systems resolving the small scale and large number of cooling holes is impractical at the preliminary design phase. This paper presents an alternative approach for predicting aerodynamic performance of TCC systems using a “smart” porous media to replace regions of cooling holes. Numerically (CFD) defined correlations have been developed, which account for geometry and local flow field, to define the porous media loss coefficient. These are coded as a user defined function allowing the loss to vary, within the calculation, as a function of the predicted flow and hence produce a spatial variation of mass flow matching that of the cooling holes. The methodology has been tested on various geometrical configurations representative of current TCC systems and compared to full cooling hole models. The method was shown to achieve good overall agreement whilst significantly reducing both the mesh count and the computational time to a practical level.
Description: This paper is closed access until 22 November 2019.
Sponsor: This research was undertaken at Loughborough University within the Rolls‐Royce University Technology Centre (UTC) in Combustion System Aero Thermal Processes. It was funded by the Aerospace Technology Institute and Rolls‐Royce plc.
Version: Accepted for publication
DOI: 10.1115/1.4041933
URI: https://dspace.lboro.ac.uk/2134/35725
Publisher Link: https://doi.org/10.1115/1.4041933
ISSN: 0742-4795
Appears in Collections:Closed Access (Aeronautical and Automotive Engineering)

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