Modeling of Film Cooling—Part I: Experimental Study of Flow Structure

[+] Author and Article Information
Stefan Bernsdorf, Martin G. Rose, Reza S. Abhari

Institute of Energy Technologies, Department of Mechanical Engineering, Swiss Federal Institute of Technology - ETHZ, CH-8092 Zurich, Switzerland

J. Turbomach 128(1), 141-149 (Feb 01, 2005) (9 pages) doi:10.1115/1.2098768 History: Received October 01, 2004; Revised February 01, 2005

This paper, which is Part I of a two part paper, reports on experimental data taken in a steady flow, flat plate wind tunnel at ETH Zürich, while Part II utilizes this data for calibration and validation purpose of a film cooling model embedded in a 3D CFD code. The facility simulates the film cooling row flow field on the pressure side of a turbine blade. Engine representative nondimensionals are achieved, providing a faithful model at larger scale. Heating the freestream air and strongly cooling the coolant gives the required density ratio between coolant and freestream. The three dimensional velocities are recorded using nonintrusive PIV; seeding is provided for both air streams. Two different cylindrical hole geometries are studied, with different angles. Blowing ratio is varied over a range to simulate pressure side film cooling. The three dimensional flow structures are revealed.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 8

Influence of IR on centerline axial velocity

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Figure 1

Schematic of test rig

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Figure 2

Sketch of test section

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Figure 3

Definition of coordinates and dimensions

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Figure 4

Schematic of injection arrangement

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Figure 9

Penetration of jet into freestream

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Figure 10

α=50 deg, BR=1, DR=1, and IR=1

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Figure 5

Mounting of PIV system

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Figure 11

α=50 deg, BR=2, DR=1, and IR=4

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Figure 12

50 deg, BR=1, DR=1, and IR=1; iso-plane U∕Uf=0.95

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Figure 13

50 deg, BR=2, DR=1, and IR=4; iso-plane U∕Uf=0.95

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Figure 6

Influence of BR and DR on axial velocity at X=4

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Figure 7

Influence of α and BR on axial velocity at X=4



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