Research Papers

Heat Transfer and Pressure Drop Measurements in a Rib Roughened Leading Edge Cooling Channel

[+] Author and Article Information
Norbert Domaschke1

Jens von Wolfersdorf

 Institut für Thermodynamik der Luftund Raumfahrt,  Universität Stuttgart, Pfaffenwaldring 31, D-70569 Stuttgart, Germanyjens.vonwolfersdorf@itlr.uni-stuttgart.de

Klaus Semmler

 Heat Transfer and Combustion,  MTU Aero Engines GmbH, D-80995 Munich, Germanyklaus.semmler@muc.mtu.de


Corresponding author.

J. Turbomach 134(6), 061006 (Aug 27, 2012) (9 pages) doi:10.1115/1.4004747 History: Received March 11, 2011; Revised July 27, 2011; Published August 27, 2012; Online August 27, 2012

In order to enhance convective heat transfer in internal cooling channels, ribs are often used to manipulate the flow field and to benefit from their effect on thermal performance. This paper presents results from an experimental investigation into pressure loss and heat transfer in a smooth and a ribbed leading edge channel of a gas turbine blade internal cooling system. To model the cross section of a realistic leading edge cooling channel both the suction side and the leading edge of the blade profile are designed as curved walls with constant radii. The pressure side as well as the web is approximated by planar walls. For the ribbed channel, 45 deg-ribs related to the flow direction are placed on the pressure and the suction side with the normalized rib height e/dh  = 0.10. Experiments have been carried out for the smooth and the ribbed channel. The flow rate was varied to cover a Reynolds number range from 20,000 to 50,000. The heat transfer has been determined using the transient liquid crystal method. Additional numerical simulations using the SST turbulence model were carried out to analyze the flow field in the channel. The computations were used for further interpretation of the experimental investigations, especially to determine the temperature field and velocity field and therefore the bulk temperature within the test section.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Turbine airfoil with ribbed triangular shaped leading edge channel

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Figure 2

Diagram of test rig

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Figure 3

Cross section of the channel

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Figure 4

Camera positions

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Figure 5

Transformation of the distorted view of the suction side

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Figure 6

Positions of thermocouples and fluid temperature histories

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Figure 7

Time invariant normalized fluid temperature field for different point of time

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Figure 8

Numerical domain and boundary conditions

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Figure 9

Comparison between normalized temperature fields resulting from experiment and numerical simulation

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Figure 10

Normalized Nusselt Number distribution of smooth channel Re = 30,000

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Figure 11

Streamlines in the channel near the suction side

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Figure 12

Pattern of velocity in a cross section

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Figure 13

Normalized Nusselt number distribution of ribbed channel for Re = 30,000

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Figure 14

Line averaged normalized Nusselt number distribution of ribbed channel for 20,000 ≤ Re ≤ 50,000

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Figure 15

Fanning friction factor for 20,000 ≤ Re ≤ 50,000

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Figure 16

Normalized friction factor for 20,000 ≤ Re ≤ 50,000

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Figure 17

Overall thermal performance for 20,000 ≤ Re ≤ 50,000



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