Heat Transfer and Film-Cooling Measurements on a Stator Vane With Fan-Shaped Cooling Holes

[+] Author and Article Information
W. Colban, A. Gratton, K. A. Thole

Mechanical Engineering Department,  Virginia Polytechnic and State University, Blacksburg, VA 24061

M. Haendler

 Siemens Power Generation, Muelheim an der Ruhr, Germany

J. Turbomach 128(1), 53-61 (Feb 01, 2005) (9 pages) doi:10.1115/1.2098789 History: Received October 01, 2004; Revised February 01, 2005

In a typical gas turbine engine, the gas exiting the combustor is significantly hotter than the melting temperature of the turbine components. The highest temperatures in an engine are typically seen by the turbine inlet guide vanes. One method used to cool the inlet guide vanes is film cooling, which involves bleeding comparatively low-temperature, high-pressure air from the compressor and injecting it through an array of discrete holes on the vane surface. To predict the vane surface temperatures in the engine, it is necessary to measure the heat transfer coefficient and adiabatic film-cooling effectiveness on the vane surface. This study presents heat transfer coefficients and adiabatic effectiveness levels measured in a scaled-up, two-passage cascade with a contoured endwall. Heat transfer measurements indicated that the behavior of the boundary layer transition along the suction side of the vane showed sensitivity to the location of film-cooling injection, which was simulated through the use of a trip wire placed on the vane surface. Single-row adiabatic effectiveness measurements without any upstream blowing showed jet lift-off was prevalent along the suction side of the airfoil. Single-row adiabatic effectiveness measurements on the pressure side, also without upstream showerhead blowing, indicated jet lifted-off and then reattached to the surface in the concave region of the vane. In the presence of upstream showerhead blowing, the jet lift-off for the first pressure side row was reduced, increasing adiabatic effectiveness levels.

Copyright © 2006 by American Society of Mechanical Engineers
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Figure 1

Schematic of the low-speed recirculating wind tunnel facility

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Figure 2

Two-passage, three-vane test section with a contoured endwall

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Figure 3

Contoured endwall surface definition

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Figure 4

Cp distribution around the vane before and after the contoured endwall compared with engine conditions (dashed lines indicate locations of film-cooling rows)

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Figure 5

The effect of span height on the Cp distribution

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Figure 6

Film-cooling vane showing hole designations

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Figure 7

Fan-shaped cooling hole detailed geometry

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Figure 8

Fan-shaped hole discharge coefficients

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Figure 9

Stanton number distribution around the vane for all span heights

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Figure 10

Trip wire locations shown relative to hole exit locations on the vane

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Figure 11

Stanton numbers for the four suction side trip cases

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Figure 12

Contours of adiabatic effectiveness for the M∞=2.9 and M∞=0.6 showerhead cases

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Figure 13

Laterally averaged effectiveness for the showerhead cases

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Figure 14

Contours of adiabatic effectiveness for high and low blowing ratios for row PD and laterally averaged adiabatic effectiveness for row PD

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Figure 15

Contours of adiabatic effectiveness for high and low blowing ratios for row PC and laterally averaged adiabatic effectiveness for rows PC‐PA

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Figure 16

Contours of adiabatic effectiveness for high and low blowing ratios for row SA and a representative case for row SD. Also laterally averaged effectiveness for the suction side rows.

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Figure 17

Comparisons with published cylindrical hole vane film-cooling data and fan-shaped flat plate data




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