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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

[+] Author and Article Information
R. M. Mathison

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235mathison.4@osu.edu

C. W. Haldeman

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235haldeman.5@osu.edu

M. G. Dunn

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235dunn.129@osu.edu

J. Turbomach 134(1), 011007 (May 25, 2011) (8 pages) doi:10.1115/1.4002995 History: Received August 17, 2010; Revised August 23, 2010; Published May 25, 2011; Online May 25, 2011

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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Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Schematic of instrument locations (not to scale)

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Figure 2

Comparison of inlet temperature profile shapes for runs without cooling

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Figure 3

Comparison of rotor inlet temperature profiles measured by blade leading edge thermocouples for runs without cooling

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Figure 4

Stanton number distributions for pressure surface with different inlet temperature profile shapes

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Figure 5

Stanton number distributions for suction surface with different inlet temperature profile shapes

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Figure 6

Stanton number distribution for blade platform with different inlet temperature profiles

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Figure 7

Comparison of platform fluid temperatures measured for different inlet temperature profiles

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Figure 8

Comparison of Stanton number for angel wing region with different inlet temperature profiles

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Figure 9

Stanton number measured for outer shroud and blade tip region with different inlet temperature profiles

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Figure 10

Surface temperature fluctuation over a full rotor revolution for gauge HR145 on pressure surface for hot streak run with nominal cooling

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Figure 11

Surface temperature fluctuation over a full rotor revolution for gauge HR150 on suction surface for hot streak run with nominal cooling

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Figure 12

FFT of surface temperature fluctuation for gauge HR150 on the blade suction surface for a hot streak run with nominal cooling

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Figure 13

Time-accurate comparison of hot streak and radial runs without cooling for HFG on suction surface

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Figure 14

Time-accurate comparison of hot streak and radial runs with nominal cooling flow rates for HFG on suction surface

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