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TECHNICAL PAPERS

Three-Dimensional Flow Prediction and Improvement of Holes Arrangement of a Film-Cooled Turbine Blade Using a Feature-Based Jet Model

[+] Author and Article Information
André Burdet, Reza S. Abhari

Turbomachinery Laboratory, Department of Mechanical and Process Engineering, Swiss Federal Institute of Technology – ETH Zürich, CH-8092 Zürich, Switzerland

J. Turbomach 129(2), 258-268 (Jun 06, 2006) (11 pages) doi:10.1115/1.2437778 History: Received June 01, 2006; Revised June 06, 2006

A feature-based jet model has been proposed for use in three-dimensional (3D) computational fluid dynamics (CFD) prediction of turbine blade film cooling. The goal of the model is to be able to perform computationally efficient flow prediction and optimization of film-cooled turbine blades. The model reproduces in the near-hole region the macroflow features of a coolant jet within a Reynolds-averaged Navier-Stokes framework. Numerical predictions of the 3D flow through a linear transonic film-cooled turbine cascade are carried out with the model, with a low computational overhead. Different cooling holes arrangements are computed, and the prediction accuracy is evaluated versus experimental data. It is shown that the present model provides a reasonably good prediction of the adiabatic film-cooling effectiveness and Nusselt number around the blade. A numerical analysis of the interaction of coolant jets issuing from different rows of holes on the blade pressure side is carried out. It is shown that the upward radial migration of the flow due to the passage secondary flow structure has an impact on the spreading of the coolant and the film-cooling effectiveness on the blade surface. Based on this result, a new arrangement of the cooling holes for the present case is proposed that leads to a better spanwise covering of the coolant on the blade pressure side surface.

Copyright © 2007 by American Society of Mechanical Engineers
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References

Figures

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Figure 15

Strategy for new hole arrangement

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Figure 16

Predicted contours of adiabatic film-cooling effectiveness η on pressure side obtained with the new hole arrangement in set 4a; MOD_A (left) and MOD_B (right)

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Figure 17

Predicted profiles of lateral adiabatic film-cooling effectiveness η on the pressure side, at X∕CAC=0.80, for the original hole arrangement and the improved hole arrangement (MOD_A)

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Figure 5

Computational mesh

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Figure 4

Geometrical dimensions of the film-cooled turbine blade (24-25)

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Figure 3

Example of two 3D film-cooling boxes with the immersed jet body. The boxes can cross each other without any impact on the solution accuracy.

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Figure 2

Sketch of the near-hole coolant jet macro flow features

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Figure 1

Schematic of the near-hole region and the main geometrical parameters

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Figure 10

Measured and predicted profiles of adiabatic film-cooling effectiveness η on suction side surface, at midspan, for BR=[1.0,1.5]

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Figure 11

Measured and predicted profiles of Nusselt number Nu at midspan for BR=[1.0,1.5]; injection at [set 1, set 3]; and S is blade surface length

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Figure 12

Predicted contours of adiabatic film-cooling effectiveness η on pressure side with injection from set 3 and set 4a (left) and superposition of injection from set 3 only and injection from set 4a only (right)

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Figure 13

Predicted contours of the normalized temperature θ and jet secondary flow vectors U2nd near the midspan region for injection at set 4a only (top), for injection at set 3 and set 4a (middle) and near the hub region for injection at set 3 and set 4a (bottom). Only every second vector is represented.

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Figure 14

Schematic of coolant jets interactions

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Figure 6

Overhead σ as a function of the number of holes Nh

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Figure 7

Predicted contours of Nusselt number and surface flow streamlines (left); measured and predicted Nusselt number distribution at midspan (right); and S is blade surface length

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Figure 8

Measured and predicted profiles of isentropic Mach number Mais at midspan

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Figure 9

Predicted contours of adiabatic film-cooling effectiveness η on suction side surface for BR=1.0 (left) and BR=1.5 (right)

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