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Research Papers

Effect of Varying Jet Diameter on the Heat Transfer Distributions of Narrow Impingement Channels

[+] Author and Article Information
Alexandros Terzis

Group of Thermal Turbomachinery (GTT),
École Polytechnique Fédérale
de Lausanne (EPFL),
Lausanne CH-1015, Switzerland
e-mail: alexandros.terzis@me.com

Peter Ott

Group of Thermal Turbomachinery (GTT),
École Polytechnique Fédérale
de Lausanne (EPFL),
Lausanne CH-1015, Switzerland

Magali Cochet

Alstom Power,
Baden CH-5401, Switzerland

Jens von Wolfersdorf, Bernhard Weigand

Institute of Aerospace Thermodynamics (ITLR),
University of Stuttgart,
Stuttgart D-70569, Germany

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 18, 2014; final manuscript received July 19, 2014; published online September 10, 2014. Editor: Ronald Bunker.

J. Turbomach 137(2), 021004 (Sep 10, 2014) (9 pages) Paper No: TURBO-14-1155; doi: 10.1115/1.4028294 History: Received July 18, 2014; Revised July 19, 2014

The development of integrally cast turbine airfoils allows the production of narrow impingement channels in a double-wall configuration, where the coolant is practically injected within the wall of the airfoil providing increased heat transfer capabilities. This study examines the cooling performance of narrow impingement channels with varying jet diameters using a single exit design in an attempt to regulate the generated crossflow. The channel consists of a single row of five inline jets tested at two different channel heights and over a range of engine representative Reynolds numbers. Detailed heat transfer coefficient distributions are evaluated over the complete interior surfaces of the channel using the transient liquid crystal technique. Additionally, local jet discharge coefficients are determined by probe traversing measurements for each individual jet. A 10%-increasing and a 10%-decreasing jet diameter pattern are compared with a baseline geometry of uniform jet size distribution, indicating a considerable effect of varying jet diameter on the heat transfer level and the development of the generated crossflow.

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References

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Figures

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Fig. 1

Narrow impingement cooling cavities within a turbine airfoil wall

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Fig. 2

Impingement cooling test facility

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Fig. 3

Narrow impingement channel models

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Fig. 4

Schematic representation of pressure measurement points (a) 10%—increasing jet diameter, (b) uniform jet diameter, and (c) 10%—decreasing jet diameter

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Fig. 5

Jet axial velocity profiles (y-direction): (a) 10%—increasing jet diameter; (b) uniform jet diameter; (c) 10%—decreasing jet diameter

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Fig. 6

Local jet discharge coefficients at ReD = 23,780, (a) ReD,j variation and (b) Gcf development

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Fig. 7

(a) ReD,j variation and (b) Gcf development

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Fig. 8

Heat transfer coefficient surface contours (h/href) for the target plate and the sidewalls at ReD = 23,780: (a) Z/D = 1.5 and (b) Z/D = 3

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Fig. 9

Local Nusselt number distributions on the channel centerline (y = 0) for the target plate at ReD = 23,780: (a) Z/D = 1.5 and (b) Z/D = 3

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Fig. 10

Heat transfer coefficient surface contours (h/href) for the impingement plate at ReD = 23,780: (a) Z/D = 1.5 and (b) Z/D = 3

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Fig. 11

Spanwise averaged NuD distributions for all channel walls at ReD = 23,780: (a) target plate, Z/D = 1.5; (b) sidewall, Z/D = 1.5; (c) impingement plate, Z/D = 1.5; (d) target plate, Z/D = 3; (e) sidewall, Z/D = 3; and (f) impingement plate, Z/D = 3

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Fig. 12

Area averaged NuD as a function of jet average Reynolds number for all channel walls: (a) Z/D = 1.5 and (b) Z/D = 3

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