Research Papers

Experimental Flow Structure Investigation of Compound Angled Film Cooling

[+] Author and Article Information
Vipluv Aga, Martin Rose

Institute for Energy Technologies, Department of Mechanical and Process Engineering,  ETH Zurich, CH-8092, Zurich, Switzerland

Reza S. Abhari

Institute for Energy Technologies, Department of Mechanical and Process Engineering,  ETH Zurich, CH-8092, Zurich, Switzerlandrabhari@ethz.ch

J. Turbomach 130(3), 031005 (May 02, 2008) (8 pages) doi:10.1115/1.2775491 History: Received July 27, 2006; Revised April 03, 2007; Published May 02, 2008

The experimental investigation of film-cooling flow structure provides reliable data for calibrating and validating a 3D feature based computational fluid dynamics (CFD) model being developed synchronously at the ETH Zurich. This paper reports on the flow structure of a film-cooling jet emanating from one hole in a row of holes angled 20 deg to the surface of a flat plate having a 45 deg lateral angle to the freestream flow in a steady flow, flat plate wind tunnel. This facility simulates a film-cooling row typically found on a turbine blade, giving engine representative nondimensionals in terms of geometry and operating conditions. The main flow is heated and the injected coolant is cooled strongly to obtain the requisite density ratio. All three velocity components were measured using a nonintrusive stereoscopic particle image velocimetry (PIV) system. The blowing ratio and density ratio are varied for a single compound angled geometry, and the complex three dimensional flow is investigated with special regard to vortical structure.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 10

Horizontal velocity isosurfaces for U∕Um=0.95 and U∕Um=1.2 at BR=2, DR=1(a1) and (a2) and BR=2, DR=1.55(b1) and (b2)

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Figure 1

Definition of coordinate system and geometrical parameters

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Figure 2

Schematic of the test rig

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Figure 3

Schematic of the injection arrangement

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Figure 4

Schematic and diagram of the stereoscopic PIV Mounting

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Figure 5

Flow vectors and contours of normalized axial velocity at X=2 for different flow conditions

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Figure 6

Streamwise vorticity isosurfaces with velocity streamlines for BR=2, DR=1, and IR=4

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Figure 7

Streamwise vorticity isosurfaces with velocity streamlines for BR=2, DR=1.55, and IR=2.6

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Figure 8

Normal vorticity for BR=2, DR=1 and BR=2, DR=1.55 at different vertical Z planes

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Figure 9

Normal vorticity for BR=3, DR=1 and BR=3, DR=1.55 at different vertical Z planes



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