Heat flux measurements are presented for the uncooled blades of a one and one-half stage turbine operating at design corrected conditions with a fully cooled upstream vane row and with rotor disk cavity purge flow. This paper highlights the differences in blade heat flux and temperature caused by uniform, radial, and hot streak inlet temperature profiles. A general discussion of temperature profile migration is provided in Part I, and Part III presents data for hot streak magnitudes and alignments. The heat flux and fluid temperature measurements for the blade airfoil, platform, angel wing (near the root), and tip as well as for the stationary outer shroud are influenced by the vane inlet temperature profile. The inlet temperature profile shape can be clearly observed in the blade Stanton number measurements, with the radial and hot streak profiles showing a greater redistribution of energy than the uniform case due to secondary flows. Hot-gas segregation is observed to increase with the strength of the temperature distortion. Measurements for the hot streak profile show a segregation of higher temperature fluid to the pressure surface when compared with a uniform profile. The introduction of vane and purge cooling is found to further accentuate the flow segregation due to coolant migration to the suction surface.
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e-mail: mathison.4@osu.edu
e-mail: haldeman.5@osu.edu
e-mail: dunn.129@osu.edu
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January 2012
Research Papers
Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine–Part II: Influence of Inlet Temperature Profile on Blade Row and Shroud
R. M. Mathison,
R. M. Mathison
Gas Turbine Laboratory,
e-mail: mathison.4@osu.edu
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235
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C. W. Haldeman,
C. W. Haldeman
Gas Turbine Laboratory,
e-mail: haldeman.5@osu.edu
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235
Search for other works by this author on:
M. G. Dunn
M. G. Dunn
Gas Turbine Laboratory,
e-mail: dunn.129@osu.edu
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235
Search for other works by this author on:
R. M. Mathison
Gas Turbine Laboratory,
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235e-mail: mathison.4@osu.edu
C. W. Haldeman
Gas Turbine Laboratory,
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235e-mail: haldeman.5@osu.edu
M. G. Dunn
Gas Turbine Laboratory,
The Ohio State University
, 2300 West Case Road, Columbus, OH 43235e-mail: dunn.129@osu.edu
J. Turbomach. Jan 2012, 134(1): 011007 (8 pages)
Published Online: May 25, 2011
Article history
Received:
August 17, 2010
Revised:
August 23, 2010
Online:
May 25, 2011
Published:
May 25, 2011
Connected Content
A companion article has been published:
Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration
Citation
Mathison, R. M., Haldeman, C. W., and Dunn, M. G. (May 25, 2011). "Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine–Part II: Influence of Inlet Temperature Profile on Blade Row and Shroud." ASME. J. Turbomach. January 2012; 134(1): 011007. https://doi.org/10.1115/1.4002995
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