Combustor Wall Axial Location Effects on First Vane Leading-Edge Cooling

Because of the highest thermal load and the complex flow interactions, the cooling of the first vane leading edge is one of the most challenging problems in gas turbine aerothermal design. In industrial gas turbines with multiple can combustors around the annulus, depending on the clocking position...

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Bibliographic Details
Published in:Journal of propulsion and power 2015-07, Vol.31 (4), p.1094-1106
Main Authors: Mazzoni, C. M, Rosic, B, Klostermeier, C
Format: Article
Language:English
Subjects:
Aerodynamics
Combustion chambers
Computational fluid dynamics
Cooling
Cooling effects
Film cooling
Flat plates
Fluid flow
Gas turbines
Leading edges
Mathematical models
Numerical prediction
Scale models
Sheds
Subgrid scale models
Thermal analysis
Trailing edges
Unsteady
Vanes
Vertical orientation
Walls
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Summary:Because of the highest thermal load and the complex flow interactions, the cooling of the first vane leading edge is one of the most challenging problems in gas turbine aerothermal design. In industrial gas turbines with multiple can combustors around the annulus, depending on the clocking position between can combustors and downstream turbine, the first vane leading edges may also be exposed to large wake disturbances shed from the upstream combustor walls. The influence of these vortical structures on the first vane leading-edge film cooling is numerically analyzed in this paper, by using the flow solver TBLOCK. The initial flow domain with the cylindrical leading edge and cooling holes, based on an experimental setup, is extended to incorporate the effect of the combustor wall, which is modeled as a flat plate with a square trailing-edge. The location and the size of the plate are scaled to be representative of industrial practice. Two different axial positions of the vertical combustor wall model are investigated and compared with the datum clean configuration. A large-eddy-simulation turbulence modeling strategy with WALE subgrid scale model is applied to analyze the wake–leading-edge interaction, dominated by large-scale unsteady vortical structures. Numerical predictions show that the shed vortices from the combustor wall trailing-edge have a highly detrimental effect on the leading-edge film cooling by periodically removing the coolant flow from the leading-edge surface. This results in an increased unsteady thermal load.
ISSN:0748-4658
1533-3876
DOI:10.2514/1.B35388