Research Papers

Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach

[+] Author and Article Information
C. W. Haldeman, R. M. Mathison, M. G. Dunn, S. A. Southworth, J. W. Harral

Gas Turbine Laboratory,  The Ohio State University, Columbus, OH 43235

G. Heitland

 Honeywell Aerospace, Phoenix, AZ 85034

J. Turbomach 130(2), 021015 (Mar 24, 2008) (10 pages) doi:10.1115/1.2750676 History: Received July 13, 2006; Revised July 16, 2006; Published March 24, 2008

This paper describes the experimental approach utilized to perform experiments using a fully cooled rotating turbine stage to obtain film effectiveness measurements. Significant changes to the previous experimental apparatus were implemented to meet the experimental objectives. The modifications include the development of a synchronized blowdown facility to provide cooling gas to the turbine stage, installation of a heat exchanger capable of generating a uniform or patterned inlet temperature profile, novel utilization of temperature and pressure instrumentation, and development of robust double-sided heat flux gauges. With these modifications, time-averaged and time-accurate measurements of temperature, pressure, surface heat flux, and film effectiveness can be made over a wide range of operational parameters, duplicating the nondimensional parameters necessary to simulate engine conditions. Data from low Reynolds number experiments are presented to demonstrate that all appropriate scaling parameters can be satisfied and that the new components have operated correctly. Along with airfoil surface heat transfer and pressure data, temperature and pressure data from inside the coolant plenums of the vane and rotating blade airfoils are presented. Pressure measurements obtained inside the vane and blade plenum chambers illustrate passing of the wakes and shocks as a result of vane/blade interaction. Part II of this paper (Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S. A., Harral, J. W., and Heltland, G., 2008, ASME J. Turbomach., 130(2), p. 021016) presents data from the low Reynolds number cooling experiments and compares these measurements to CFD predictions generated using the Numeca FINE/Turbo package at multiple spans on the vanes and blades.

Copyright © 2008 by American Society of Mechanical Engineers
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Figure 1

Honeywell turbine in TTF

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Figure 3

Turbine cooling paths

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Figure 4

Vane cooling hole pattern

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Figure 5

Blade cooling holes

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Figure 6

Blade suction side, 50% span instruments

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Figure 7

Large cooling facility

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Figure 8

Schematic of cooling connections

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Figure 10

Overall matrix temperature

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Figure 11

Cooling experiment time history

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Figure 12

Corrected speed variation

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Figure 13

Overall stage pressures and pressure ratio

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Figure 14

Rake temperatures at design point

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Figure 15

Cooling gas internal pressures

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Figure 16

Internal temperatures

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Figure 17

Normalized rotor pressures

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Figure 18

Power spectrum of internal rotor pressures





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