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Gas Turbines: Combustion, Fuels, and Emissions

Large-Eddy Simulation of Flow and Convective Heat Transfer in a Gas Turbine Can Combustor With Synthetic Inlet Turbulence

[+] Author and Article Information
Sunil Patil, Danesh Tafti

 Virginia Tech, Blacksburg, VA 24061

J. Eng. Gas Turbines Power 134(7), 071503 (May 23, 2012) (9 pages) doi:10.1115/1.4006081 History: Received December 10, 2011; Revised January 28, 2012; Published May 23, 2012; Online May 23, 2012

Large eddy simulations of swirling flow and the associated convective heat transfer in a gas turbine can combustor under cold flow conditions for Reynolds numbers of 50,000 and 80,000 with a characteristic Swirl number of 0.7 are carried out. A precursor Reynolds averaged Navier-Stokes (RANS) simulation is used to provide the inlet boundary conditions to the large-eddy simulation (LES) computational domain, which includes only the can combustor. A stochastic procedure based on the classical view of turbulence as a superposition of the coherent structures is used to simulate the turbulence at the inlet plane of the computational domain using the mean flow velocity and Reynolds stress data from the precursor RANS simulation. To further reduce the overall computational resource requirement and the total computational time, the near wall region is modeled using a zonal two layer model (WMLES). A novel formulation in the generalized co-ordinate system is used for the solution of effective tangential velocity and temperature in the inner layer virtual mesh. The WMLES predictions are compared with the experimental data of Patil (2011, “Experimental and Numerical Investigation of Convective Heat Transfer in Gas Turbine Can Combustor,” ASME J. Turbomach., 133 (1), p. 011028) for the local heat transfer distribution on the combustor liner wall obtained using robust infrared thermography technique. The heat transfer coefficient distribution on the liner wall predicted from the WMLES is in good agreement with experimental values. The location and the magnitude of the peak heat transfer are predicted in very close agreement with the experiments.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Wall normal virtual grid for wall model, embedded in the LES grid (P is the off wall outer LES node and W is the normal projection of P on the wall)

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Figure 2

Schematics of the experimental setup of Patil [7]. From left to right: swirler, nozzle extension channel, and can combustor. The RANS domain is shown in solid lines. The LES domain is shown in dotted lines and the interface between the RANS and LES is shown by the dashed line.) (L* = D = 203 mm, H = 0.3 D) (Swirl nozzle details: Ri = 0.11 D, Ro  = 0.2 D).

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Figure 3

3D computational domain: (a) frontal view of the mesh, and (b) side view of the mesh

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Figure 4

Profiles of the mean velocity (normalized by the bulk mean velocity in the combustor) and the turbulent kinetic energy (normalized by the square of the bulk mean velocity in the combustor) at the inlet plane of the LES computational domain (x/H= −0.5) (Re = 50,000, Swirl number = 0.7)

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Figure 5

(a) Mean flow streamlines in the azimuthal plane (z = 0), and (b) contours of the axial velocity (normalized by the bulk mean combustor velocity) in the azimuthal plane (z = 0) (Re = 50,000)

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Figure 6

Streamlines in an instantaneous flowfield at the (a) azimuthal plane (z = 0), and (b) streamwise location x/D = 0.5 (Re = 50,000)

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Figure 7

Variation of mean velocity components and the Reynolds stresses at (a) x/D = 0.1, (b) x/D = 0.45, and (c) x/D = 2 (scale 6:1) (Re = 50,000). All quantities are circumferentially averaged and plotted along the radial direction. Mean velocities are normalized by the bulk mean combustor velocity while the Reynolds stresses are normalized by the square of the bulk mean combustor velocity. Graphs are obtained by plotting the normalized values around the vertical lines at x axis values of 0, 1, 2, 3, 5, and 6.

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Figure 8

Heat transfer augmentation ratio (Nu/Nu0 ) along the liner wall (Re = 50,000)

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Figure 9

(a) Mean flow streamlines in the azimuthal plane (z = 0), and (b) contours of the axial velocity (normalized by the bulk mean combustor velocity) in the azimuthal plane (z = 0) (Re = 80,000)

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Figure 10

Variation of the mean velocity components and the Reynolds stresses at (a) x/D = 0.1, (b) x/D = 0.45, and (c) x/D = 2 (scale 6:1) (Re = 80,000)

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Figure 11

Heat transfer augmentation ratio (Nu/Nu0 ) along the liner wall (Re = 80,000)

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