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Research Papers

Block-Spectral Approach to Film-Cooling Modeling

[+] Author and Article Information
L. He

Department of Engineering Science, Osney Laboratory, University of Oxford, Oxford OX1 3PJ, UK

J. Turbomach 134(2), 021018 (Jun 29, 2011) (8 pages) doi:10.1115/1.4003073 History: Received July 23, 2010; Revised August 05, 2010; Published June 29, 2011; Online June 29, 2011

Gas turbine performance improvement requires efficient and accurate prediction tools for film-cooling of high pressure turbine blades. Use of computational fluid dynamics in the cooling design faces a challenge due to a wide range of length scales to be resolved. The difficulty is also seriously compounded by the basic feature that each blade has a large number of cooling holes. In the present paper, a new spectral approach is proposed to address this modeling difficulty. The motivation is to resolve the aerothermal flow field and mixing process of film-cooling by the numerical solution to the first principle based governing equations while avoiding large computational resources required in directly solving a large number of cooling holes. By using a spectral representation for each corresponding mesh point, the block-to-block (hole-to-hole) variation can be accurately and efficiently modeled. The number of mesh blocks (cooling holes) to be solved is then dictated by the number of unknowns required to determine the spectrum. Consequently, the aerothermal field for a large number of cooling hole blocks can be obtained by solving a much smaller set of blocks. The modeling consideration, method formulation, validation, and demonstration results will be presented.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 2

Mesh points linkage for constructing a four-block spectrum for point (i, j)

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Figure 12

Instantaneous temperature contours (ωt=0 deg): (a) direct solution and (b) spectral solution

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Figure 17

Hub surface temperature contours: (a) direct solution and (b) spectral solution

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Figure 1

Multiholes and equivalent single dynamic hole: (a) multiple holes and (b) single dynamic marching hole

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Figure 7

Stagnation temperature contours, direct solution (39 holes) and spectral solution (four holes): (a) direction solution and (b) block-spectral solution

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Figure 8

Static pressure contours, direct solution (39 holes) and spectral solution (four holes): (a) direction solution and (b) block-spectral solution

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Figure 9

Stagnation temperature distributions along the mesh line overlapping with wall surface on hot side

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Figure 10

Stagnation temperature contours (extended exit mesh blocks): (a) direct solution and (b) spectral solution (red-colored holes are not solved)

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Figure 11

Stagnation temperature distributions on wall surface on hot side (extended exit mesh blocks)

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Figure 13

Instantaneous temperature contours (ωt=180 deg): (a) direct solution and (b) spectral solution

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Figure 14

Computational mesh and configuration: (a) hot and cold domains and (b) hot part with cooling holes

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Figure 15

Surface temperature contours: (a) direct solution and (b) spectral solution

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Figure 16

Computational mesh (NGV, view of hub surface)

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Figure 3

Even-function periodic distribution by mirroring

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Figure 4

Block-spectral model as implemented in a time-marching RANS solver

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Figure 5

Extended mesh blocking to region of strong coolant-mainstream mixing

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Figure 6

Computational configuration and mesh

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