Research Papers: Jets, Wakes, and Impingment Cooling

The Subgrid-Scale Approach for Modeling Impingement Cooling Flow in the Combustor Pedestal Tile

[+] Author and Article Information
Dalila Ammour

Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, UK
e-mail: d.ammour@lboro.ac.uk

Gary J. Page

Professor of Computational Aerodynamics
Department of Aeronautical and
Automotive Engineering,
Loughborough University,
Loughborough LE11 3TU, UK
e-mail: g.j.page@lboro.ac.uk

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF HEAT TRANSFER. Manuscript received July 26, 2016; final manuscript received August 11, 2017; published online December 27, 2017. Assoc. Editor: George S. Dulikravich.

J. Heat Transfer 140(4), 042203 (Dec 27, 2017) (9 pages) Paper No: HT-16-1476; doi: 10.1115/1.4038210 History: Received July 26, 2016; Revised August 11, 2017

The widely used gas turbine combustor double-walled cooling scheme relies on very small pedestals. In a combustor it is impractical for computational fluid dynamics (CFD) to resolve each pedestal individually as that would require a very large amount of grid points and consequent excessive computation time. These pedestals can be omitted from the mesh and their effects captured on the fluid via a pedestal subgrid-scale (SGS) model. The aim is to apply the SGS approach, which takes into account the effects on pressure, velocity, turbulence, and heat transfer, in an unstructured CFD code. The flow inside a two-dimensional (2D) plain duct is simulated to validate the pedestal SGS model, and the results for pressure, velocity, and heat transfer are in good agreement with the measured data. The conjugate heat transfer inside a three-dimensional (3D) duct is also studied to calibrate the heat source term of the SGS model due to the pedestals. The resolved flow in the combustor pedestal tile geometry is numerically investigated using Reynolds-averaged Navier–Stokes (RANS) and large eddy simulation (LES) in order to first assess the viability of the RANS and LES to predict the impinging flow and second to provide more validation data for the development of the SGS pedestal correlations. It is found that the complexity of such a flow, with high levels of curvature, impingement, and heat transfer, poses a challenge to the standard RANS models. The LES provides more details of the impinging flow features. The pedestal model is then applied to the complete tile to replace the pedestals. The results are close to both the fully resolved CFD and the measurements. To improve the flow features in the impingement zone, the first two rows were resolved with the mesh and combined with the SGS modeling for the rest of the tile; this gave optimum results of pressure, velocity, and turbulence kinetic energy (TKE) distribution inside the pedestal cooling tile.

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Fig. 1

Experiment setup [5], CFD geometry, mesh and boundary conditions of the 2D duct

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Fig. 2

Normalized static pressure profiles at the midheight of the duct

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Fig. 3

Normalized streamwise velocity profile along the height of the duct at X/L = 0.7

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Fig. 4

Geometry, mesh, and boundary conditions of the 3D duct

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Fig. 5

Temperature contours at the vertical midsection: (a) duct with resolved pedestals, (b) SGS modeled plain duct, and (c) SGS modeled plain duct (LUFF [4] multiblock code)

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Fig. 6

Nu development along the streamwise line of the 2D duct

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Fig. 7

Geometry, dimensions, and boundary conditions of the pedestal tile

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Fig. 8

Computational mesh of the combustor pedestal tile

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Fig. 10

Normalized velocity magnitude contours at the horizontal midsection, LES results: (a) instantaneous and (b) time-averaged

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Fig. 11

Normalized velocity magnitude contours at the horizontal midsection, SST results

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Fig. 12

Normalized velocity profiles at two probes inside the tile: (a) probe A1 and (b) probe A2

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Fig. 13

Contour plots of HTCs at the hot surface of the tile: (a) Exp. of Thorpe [2], (b) LES, (c)SST, and (d) realizable kε

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Fig. 14

Profiles of streamwise-averaged HTCs along the hot plate at Y/W = 0.85

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Fig. 9

Temporal evolution of LES

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Fig. 15

Normalized pressure contours: (a) tile with resolved pedestals, (b) SGS fully modeled, and (c) resolved + SGS modeled

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Fig. 16

Normalized static pressure profiles along the hot surface

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Fig. 17

HTC contours: (a) tile with resolved pedestals, (b) SGS fully modeled, and (c) resolved + SGS modeled

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Fig. 18

HTC profiles along the hot surface



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