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.
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April 2008
Research Papers
Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach
C. W. Haldeman,
C. W. Haldeman
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
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R. M. Mathison,
R. M. Mathison
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
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M. G. Dunn,
M. G. Dunn
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
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S. A. Southworth,
S. A. Southworth
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
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J. W. Harral,
J. W. Harral
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
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G. Heitland
G. Heitland
Honeywell Aerospace
, Phoenix, AZ 85034
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C. W. Haldeman
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
R. M. Mathison
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
M. G. Dunn
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
S. A. Southworth
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
J. W. Harral
Gas Turbine Laboratory,
The Ohio State University
, Columbus, OH 43235
G. Heitland
Honeywell Aerospace
, Phoenix, AZ 85034J. Turbomach. Apr 2008, 130(2): 021015 (10 pages)
Published Online: March 24, 2008
Article history
Received:
July 13, 2006
Revised:
July 16, 2006
Published:
March 24, 2008
Connected Content
A companion article has been published:
Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part II: Experimental Results
Citation
Haldeman, C. W., Mathison, R. M., Dunn, M. G., Southworth, S. A., Harral, J. W., and Heitland, G. (March 24, 2008). "Aerodynamic and Heat Flux Measurements in a Single-Stage Fully Cooled Turbine—Part I: Experimental Approach." ASME. J. Turbomach. April 2008; 130(2): 021015. https://doi.org/10.1115/1.2750676
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